AD 2011-15-11

[Federal Register Volume 76, Number 147 (Monday, August 1, 2011)]
[Rules and Regulations]
[Pages 45657-45666]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-18242]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0450; Directorate Identifier 2011-CE-010-AD; 
Amendment 39-16758; AD 2011-15-11]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company (Cessna) Models 
337, 337A (USAF 02B), 337B, 337C, 337D, 337E, T337E, 337F, T337F, 337G, 
T337G, M337B, F 337E, FT337E, F 337F, FT337F, F 337G, and FT337GP 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD requires inspecting the wings for 
internal and external damage, repairing any damage, reinforcing the 
wings, installing operational limitation placards in the cockpit, and 
adding limitations to the airplane flight manual supplement. This AD 
was prompted by a review of installed Flint Aero, Inc. wing tip 
auxiliary fuel tanks, Supplemental Type Certificate (STC) SA5090NM. We 
are issuing this AD to detect and correct damage in the wings and to 
prevent overload failure of the wing due to the installation of the 
STC. Damage in the wing or overload failure of the wing could result in 
structural failure of the wing, which could result in loss of control.

DATES: This AD is effective September 6, 2011.

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    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of September 6, 
2011.

ADDRESSES: For service information identified in this AD, contact Flint 
Aero, Inc., 1942 Joe Crosson Drive, El Cajon, CA 92020; phone: (619) 
448-1551; fax: (619) 448-1571; Internet: http://www.flintaero.com. You 
may review copies of the referenced service information at the FAA, 
Small Airplane Directorate, 901 Locust, Kansas City, MO 64106. For 
information on the availability of this material at the FAA, call (816) 
329-4148.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dara Albouyeh, Aerospace Engineer, 
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Blvd., 
Lakewood, CA 90712; phone: (562) 627-5222; fax: (562) 627-5210; e-mail: 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on May 4, 2011 (76 FR 
25264). That NPRM proposed to require inspecting the wings for internal 
and external damage, repairing any damage, reinforcing the wings, 
installing operational limitation placards in the cockpit, and adding 
limitations to the Flint Aero, Inc. Airplane Flight Manual Supplement.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Request To Remove Certain Steps From Appendix 1

    Dennis L. Hamblin from Flint Aero, Inc. stated that steps 11, 13, 
and 14 should be removed from Appendix 1 of this AD. The inspection 
procedures in Appendix 1 are focused on damage caused by trimming of 
the close-out rib to allow passage of the fuel line. The Flint Aero, 
Inc. STC kit provides a close-out rib that replaces the Cessna close-
out rib. This configuration allows for the passage of the fuel line. 
Additionally, the Flint Aero, Inc. STC kit provides reinforcement 
doublers for all added inspection openings/cutouts; therefore, there 
should be no unreinforced cutouts.
    We do not agree with the commenter. All steps in Appendix 1 are 
required to check for any damage to the affected close-out rib, spar 
cap, and cut-outs that may have been caused by an overload condition 
regardless of the STC installation configuration.
    We have not changed the final rule AD action based on this comment.

 Request To Incorporate Revised Service Information

    Flint Aero, Inc. issued a revision to Service Bulletin FA2 to 
correct a part number reference. We inferred that Flint Aero, Inc. 
wanted the FAA to include reference to the revised service bulletin 
into the final rule AD action.
    We agree. We have revised the final rule AD action to incorporate 
the revised service bulletin.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the change described previously and any minor editorial 
changes. We have determined that these minor changes:
     [Agr]re consistent with the intent that was proposed in 
the NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 33 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
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                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
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Inspection of the wing for       5 work-hours x $85   Not applicable....  $425 per            $14,025 per
 damage.                          per hour = $425                          inspection cycle.   inspection cycle.
                                  per inspection
                                  cycle.
Fabricating and installing       1 work-hour x $85    Not applicable....  $85...............  $2,805.
 placards in the cockpit.         per hour = $85.
Modifying the Limitations        .5 work-hour x $85   Not applicable....  $42.50............  $1,402.50.
 section of the Flint Aero,       per hour = $42.50.
 Inc. Airplane Flight Manual
 Supplement.
Reinforcing the upper wing       25 work-hours x $85  $1,070............  $3,195............  $105,435.
 skin, stringer, and wing front   per hour = $2,125.
 spar cap.
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on

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products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2011-15-11 Cessna Aircraft Company: Amendment 39-16758; Docket No. 
FAA-2011-0450; Directorate Identifier 2011-CE-010-AD.

(a) Effective Date

    This AD is effective September 6, 2011.

(b) Affected ADs

    AD 2010-21-18, Amendment 39-16478, is related to the subject of 
this AD.

(c) Applicability

    This AD applies to Cessna Aircraft Company (Cessna) Models 337, 
337A (USAF 02B), 337B, 337C, 337D, 337E, T337E, 337F, T337F, 337G, 
T337G, M337B, F 337E, FT337E, F 337F, FT337F, F 337G, and FT337GP 
airplanes, all serial numbers, that:
    (1) Are certificated in any category; and
    (2) Are or have ever been modified by Flint Aero, Inc. 
Supplemental Type Certificate (STC) SA5090NM.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57; Wings.

(e) Unsafe Condition

    This AD was prompted by a review of installed Flint Aero, Inc. 
wing tip auxiliary fuel tanks, STC SA5090NM. We are issuing this AD 
to detect and correct damage in the wings and to prevent overload 
failure of the wing due to the installation of the STC. Damage in 
the wing or overload failure of the wing could result in structural 
failure of the wing, which could result in loss of control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Within the next 50 hours time-in-service (TIS) after 
September 6, 2011 (the effective date of this AD) or within 30 days 
after September 6, 2011 (the effective date of this AD), whichever 
occurs first, do a general and focused inspection of the left and 
right wing for internal and external damage at wing stations (WSTA) 
150 and 177. Do the inspections following Appendix 1 of this AD.
    (2) After the inspection required in paragraph (g)(1) of this AD 
if no damage was found and before the modification required in 
paragraph (g)(5) of this AD is incorporated, anytime severe and/or 
extreme turbulence is encountered during flight, before the next 
flight do a focused inspection of the wing for damage following 
steps 1, 2, 3, 4, 7, and 10 in Appendix 1 of this AD. Also inspect 
for signs of distress in the upper front spar in the area around 
WSTA 150 and 177. The definition of severe and extreme turbulence 
can be found in table 7-1-9 of the FAA Aeronautical Information 
Manual (AIM). You may obtain a copy of the FAA AIM at http://www.faa.gov/air_traffic/publications/atpubs/aim/.
    (3) For airplanes that have not had the modification specified 
in paragraphs (g)(4) and (g)(5) incorporated, within the next 50 
hours time-in-service (TIS) after September 6, 2011 (the effective 
date of this AD) or within 30 days after September 6, 2011 (the 
effective date of this AD), fabricate a placard (using at least \1/
8\-inch letters) with the following words and install the placard on 
the instrument panel within the pilot's clear view:
    (i) ``MAINTAIN AT LEAST 12 GAL OF FUEL IN EACH WING TIP FUEL 
TANK FOR AIRPLANE WEIGHTS BETWEEN 3,400 LBS AND 4,330 LBS.''
    (ii) ``MAINTAIN FULL FUEL IN EACH WING TIP FUEL TANK FOR 
AIRPLANE WEIGHTS AT OR ABOVE 4,330 LBS.''
    (4) If damage or signs of distress are found during the 
inspections required in paragraphs (g)(1) and (g)(2) of this AD, 
before further flight do the following:
    (i) Repair all damaged and distressed parts following FAA 
Advisory Circular (AC) 43.13-1B, Chapter 4, which can be found at 
http://rgl.faa.gov/;
    (ii) Incorporate the modification reinforcement specified in 
Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 2011, 
or Flint Aero, Inc. Service Bulletin FA2, Rev 3, dated May 3, 2011, 
following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011;
    (iii) Remove the placard specified in paragraph (g)(3) of this 
AD;
    (iv) Fabricate a new placard (using at least \1/8\-inch letters) 
with the following words and install the placard on the instrument 
panel within the pilot's clear view: ``MAINTAIN AT LEAST 12 GAL OF 
FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS AT OR ABOVE 
4,330 LBS''; and
    (v) Incorporate the information from Appendix 2 of this AD into 
the Limitations section of the Flint Aero, Inc. Airplane Flight 
Manual Supplement.
    (5) If no damage or signs of distress are found during the 
inspections required in paragraphs (g)(1) and (g)(2) of this AD, 
within the next 100 hours TIS after September 6, 2011 (the effective 
date of this AD) or within 12 months after September 6, 2011 (the 
effective date of this AD), whichever occurs first, do the 
following:
    (i) Incorporate the modification reinforcement specified in 
Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 2011, 
or Flint Aero, Inc. Service Bulletin FA2, Rev 3, dated May 3, 2011, 
following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011;
    (ii) Remove the placard specified in paragraph (g)(3) of this 
AD;
    (iii) Fabricate a new placard (using at least 1/8-inch letters) 
with the following words and install the placard on the instrument 
panel within the pilot's clear view: ``MAINTAIN AT LEAST 12 GAL OF 
FUEL IN EACH WING TIP FUEL TANK FOR AIRPLANE WEIGHTS AT OR ABOVE 
4,330 LBS''; and
    (iv) Incorporate the information from Appendix 2 of this AD into 
the Limitations section of the Flint Aero, Inc. Airplane Flight 
Manual Supplement.
    (6) You may incorporate the modification reinforcement specified 
in Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 
2011, or Flint Aero, Inc. Service Bulletin FA2, Rev 3, dated May 3, 
2011, following Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 
2011, at any time after the inspection required in paragraph (g)(1) 
of this AD but no later than the compliance time specified in 
paragraph (g)(5) of this AD as long as no cracks were found. As 
required in paragraph (g)(4) of this AD, the modification 
reinforcement must be incorporated before further flight if damage 
or signs of distress are found.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as

[[Page 45660]]

appropriate. If sending information directly to the manager of the 
ACO, send it to the attention of the person identified in the 
Related Information section of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(i) Related Information

    For more information about this AD, contact Dara Albouyeh, 
Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., 
Lakewood, CA 90712; phone: (562) 627-5222; fax: (562) 627-5210; e-
mail: [email protected].

(j) Material Incorporated by Reference

    (1) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the 
following service information on September 6, 2011:
    (i) Flint Aero, Inc. Service Bulletin FA2, Rev 2, dated April 8, 
2011;
    (ii) Flint Aero, Inc. Service Bulletin FA2, Rev 3, dated May 3, 
2011; and
    (iii) Flint Aero, Inc. Drawing FA2, Rev A, dated April 8, 2011.
    (2) For service information identified in this AD, contact Flint 
Aero, Inc., 1942 Joe Crosson Drive, El Cajon, CA 92020; phone: (619) 
448-1551; fax: (619) 448-1571; Internet: http://www.flintaero.com.
    (3) You may review copies of the referenced service information 
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, MO 
64106. For information on the availability of this material at the 
FAA, call (816) 329-4148.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Appendix 1 to AD 2011-15-11

General and Focused Inspection Procedures

    Perform a general and focused inspection of the wing for 
internal and external damage from wing station (WSTA) 23 to the wing 
tip. The general inspection must be performed in accordance with 14 
CFR 43.15(c), using a checklist that includes at least the scope and 
detail of the items contained in Appendix D of 14 CFR part 43. The 
focused inspection must include the items listed below. Remove all 
wing access panels to conduct the inspections. Do these inspections 
following the manufacturer's service information and any other 
appropriate guidance, such as FAA Advisory Circular (AC) 43.13-1B 
Acceptable Methods, Techniques, and Practices--Aircraft Inspection 
and Repair. AC 43.13-1B can be found at http://rgl.faa.gov/.
    Focused inspection items to look for:
    (1) Wrinkles in upper wing skins, from the outboard edge on the 
fuel tank access covers (WSTA 150 or 177) to the WSTA 222 (See View 
B, Figure 3).
    (2) Wrinkles in the upper wing skins from WSTA 55 to 66, 
adjacent to the booms (See View E, Figure 6).
    (3) Cracking of the upper wing skins. Pay particular attention 
to any wrinkles, the radius between stiffeners at WSTA 150 (under 
fuel tank covers), and unreinforced access holes (See View B, Figure 
3).
    (4) Working (smoking) rivets outboard of the wing tank access 
covers.
    (5) Fasteners with less than two diameters edge distance.
    (6) Fasteners with less than four diameters center to center 
spacing.
    (7) Looseness of attachments of the tip extension to the wing 
and wing tip to wing extension when pushing up and down on the tip.
    (8) Any signs of distress along both front and rear spars, 
particularly in the area around WSTA 177.
    (9) Inspect under any repairs to the upper skins, particularly 
in the area just outboard of the fuel tank access covers as these 
may be covering up existing damage.
    (10) Inter-rivet buckling of the stringers attached to the upper 
surface skin, outboard of the fuel tank access covers (See View F, 
Figure 7).
    (11) Inspect rib at WSTA 222 for damage. Trimming of the rib may 
have been done to allow installation of fuel lines (See View A, 
Figure 2). Repair in accordance with AC 43.13-1B, Chapter 4, 
paragraph 4-58(g) and Figure 4-14, or by using another FAA-approved 
method that restores equivalent strength of the wing rib.

Appendix 1 to AD 2011-15-11

General and Focused Inspection Procedures (Continued)

    (12) Inspect and identify screws, installed in tapped (threaded) 
holes in metal substructure, used to attach wing tips, stall fences, 
fuel and electrical components, and access doors. For tapped holes, 
remove fastener and open up the diameter to provide a smooth bore 
hole, for the smallest oversize fastener, using close tolerance 
holes noted in AC 43.13-1B, paragraph 7-39 or other FAA-approved 
scheme. Maintain minimum 2 x fastener diameter edge distance and 4 x 
fastener diameter center to center spacing. Select and install new, 
equivalent strength or stronger, fasteners with nuts/collars in 
accordance with AC 43.13-1B, Chapter 7 and AC 43.13-2B, paragraph 
108 or other FAA-approved repair. New fasteners must not have 
threads in bearing against the sides of the holes.
    (13) Inspect wing skins for unreinforced cutouts. (See View C, 
Figure 4).
    (14) Inspect the upper spar cap horizontal flanges for open 
holes (See View D, Figure 5).
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Appendix 2 to AD 2011-15-11

    Airworthiness Limitations for the Flint Aero, Inc. Airplane 
Flight Manual Supplement.
    ``MAINTAIN AT LEAST 12 GAL OF FUEL IN EACH WING TIP FUEL TANK 
FOR AIRPLANE WEIGHTS AT OR ABOVE 4,330 LBS.''

    Issued in Kansas City, Missouri, on July 14, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011-18242 Filed 7-29-11; 8:45 am]
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