[Federal Register Volume 77, Number 26 (Wednesday, February 8, 2012)]
[Proposed Rules]
[Pages 6522-6525]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-2911]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0105; Directorate Identifier 2011-NM-123-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 777 airplanes. This proposed AD was 
prompted by reports of fractured and missing latch pin retention bolts 
that secure the latch pins on the forward cargo door. This proposed AD 
would require repetitive detailed inspections for fractured or missing 
latch pin retention bolts, replacement of existing titanium bolts with 
new Inconel bolts, and related investigative and corrective actions if 
necessary. We are proposing this AD to detect and correct fractured and 
missing latch pin retention bolts, which could result in potential 
separation of the cargo door from the airplane and catastrophic 
decompression of the airplane.

DATES: We must receive comments on this proposed AD by March 26, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
(206) 544-5000, extension 1; fax (206) 766-5680; email 
[email protected]; Internet https://www.myboeingfleet.com. You may 
review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call (425) 227-1221.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Ana Martinez Hueto, Aerospace 
Engineer, Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: (425) 917-6592; fax: (425) 917-6590; email: 
[email protected].

[[Page 6523]]


SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2012-0105; 
Directorate Identifier 2011-NM-123-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received reports of fractured and missing latch pin 
retention bolts that secure the latch pins on the forward cargo door. 
Two adjacent latch pins that migrate from their position, or are broken 
in close proximity, are not able to hold the door closed for the design 
loads. Fractured and missing latch pin retention bolts, if not detected 
and corrected, could result in potential separation of the cargo door 
from the airplane and catastrophic decompression of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 777-52A0038, Revision 1, 
dated June 24, 2010. This service information describes procedures for 
repetitive detailed inspections for fractured or missing latch pin 
retention bolts, and related investigative and corrective actions if 
necessary.
    Related investigative actions include measuring the migration 
distance of the latch pins; a detailed inspection for any crack or 
surface depression of the latch pin retention bolt hole; a detailed 
inspection for any crack or damage of the lower sill of the forward 
large cargo door, fuselage frames, internal and external skin of the 
fuselage, cargo door frames, mid-span latch cam (if installed), and 
main cam latch mechanisms; and a detailed inspection for any cut, 
crack, or damage of the main cam latch of the cargo door.
    Corrective actions include contacting Boeing for repair 
instructions; repairing; changing the installed bolt head direction; 
applying the specified torque to the retention bolts to check for loose 
bolts; replacing existing latch pin retention bolts made of titanium 
with new Inconel bolts; replacing the latch pin fitting assembly; 
repairing the lower sill of the forward large cargo door, fuselage 
frames, internal and external skin of the fuselage, cargo door frames, 
mid-span latch cam, and main cam latch mechanisms; and replacing the 
cargo door main cam latch, if necessary.
    Replacing latch pin retention bolts made of titanium with new 
Inconel bolts, if accomplished, would eliminate the need for repetitive 
inspections for that area only.
    For the detailed inspections for fractured or missing latch pin 
retention bolts, the service information specifies an initial 
compliance time of within 12 months after the Revision 1 issue date, 
and a repetitive interval of 1,000 flight cycles.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously.

Differences Between the Proposed AD and the Service Information

    Boeing Alert Service Bulletin 777-52A0038, Revision 1, dated June 
24, 2010, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this proposed AD would require 
repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 148 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection..........................  1 work-hour x $85 per                $0              $85          $12,580
                                       hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Cross-bolt replacement......................  2 work-hours x $85 per hour =                $50             $220
                                               $170.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

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

[[Page 6524]]

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 products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    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]

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

The Boeing Company: Docket No. FAA-2012-0105; Directorate Identifier 
2011-NM-123-AD.

(a) Comments Due Date

    We must receive comments by March 26, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes; certificated in any 
category; as identified in Boeing Alert Service Bulletin 777-
52A0038, Revision 1, dated June 24, 2010.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 52, Doors.

(e) Unsafe Condition

    This AD was prompted by reports of fractured and missing latch 
pin retention bolts that secure the latch pins on the forward cargo 
door. We are issuing this AD to detect and correct fractured and 
missing latch pin retention bolts, which could result in potential 
separation of the cargo door from the airplane and catastrophic 
decompression of the airplane.

(f) Compliance

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

(g) Inspect Retention Bolt of Latch Pin Fittings No. 1 Through No. 8

    At the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-52A0038, 
Revision 1, dated June 24, 2010, except as specified in paragraph 
(i) of this AD: Do a detailed inspection for fractured and/or 
missing latch pin retention bolts of the latch pin fittings of the 
lower sill of the forward large cargo door, and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
52A0038, Revision 1, dated June 24, 2010, except as provided by 
paragraph (h) of this AD. Do all applicable related investigative 
and corrective actions at the applicable times specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
777-52A0038, Revision 1, dated June 24, 2010. Repeat the inspection 
thereafter at the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-52A0038, 
Revision 1, dated June 24, 2010, except as specified in paragraph 
(j) of this AD.

(h) Repair

    If any cut, crack, or damage is found during any inspection 
required by this AD, and Boeing Alert Service Bulletin 777-52A0038, 
Revision 1, dated June 24, 2010, specifies to contact Boeing for 
appropriate action: Before further flight, repair the cut, crack, or 
damage in accordance with a method approved by the Manager, Seattle, 
Aircraft Certification Office (ACO), FAA. For a repair method to be 
approved, the repair must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.

(i) Exception to Compliance Time

    Where Boeing Alert Service Bulletin 777-52A0038, Revision 1, 
dated June 24, 2010, specifies a compliance time after the date on 
that service bulletin, this AD requires compliance within the 
specified compliance time after the effective date of this AD.

(j) Optional Terminating Action for Repetitive Inspections

    Replacing latch pin retention bolts made of titanium with new 
Inconel bolts, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 777-52A0038, Revision 1, dated June 
24, 2010, terminates the repetitive inspections required by 
paragraph (g) of this AD at Stations 509.10, 522.75, 537.50, 554.30, 
562.90, 579.70, 591.25, and 604.90, latch pin fittings No. 1 through 
No. 8.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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 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. Information may be emailed to: [email protected].
    (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.

(l) Related Information

    (1) For more information about this AD, contact Ana Martinez 
Hueto, Aerospace Engineer, Cabin Safety and Environmental Systems 
Branch, ANM-150S, FAA, Seattle Aircraft Certification Office, 1601 
Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6592; fax: 
(425) 917-6590; email: [email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
(206) 544-5000, extension 1; fax (206) 766-5680; email 
[email protected]; Internet https://www.myboeingfleet.com. You 
may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call (425) 227-1221.


[[Page 6525]]


    Issued in Renton, Washington on January 27, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-2911 Filed 2-7-12; 8:45 am]
BILLING CODE 4910-13-P