Airworthiness Directives; The Boeing Company Airplanes, 36222-36224 [2012-14806]

Download as PDF 36222 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules (ii) If there is no corrosion, apply touch up protective treatment, if required, and renew the bead of any damaged sealing compound in the upper part of the anchor fitting. DEPARTMENT OF TRANSPORTATION (e) Alternative Methods of Compliance (AMOC) 14 CFR Part 39 (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–4389; email: rao.edupaganti@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (f) Additional Information (1) Eurocopter Repair Sheet 365–63–36–08, dated April 4, 2008 and Standard Practices Manual (MTC) Work Cards 20.04.04, 20.04.05, and 20.05.01, which are not incorporated by reference, contain additional information regarding the subject of this proposed AD and in particular regarding the procedures for corrosion repair, protective treatment touch-up, and renewing the damaged sealing bead. (2) For service information identified in this AD, contact American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at https:// www.eurocopter.com. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (3) The subject of this AD is addressed in European Aviation Safety Agency AD No. 2011–0127, dated July 1, 2011. (g) Subject Joint Aircraft Service Component (JASC) Code: 6320: Main Rotor Gearbox. Issued in Fort Worth, Texas, on June 7, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–14805 Filed 6–15–12; 8:45 am] TKELLEY on DSK3SPTVN1PROD with PROPOSALS BILLING CODE 4910–13–P VerDate Mar<15>2010 16:48 Jun 15, 2012 Jkt 226001 Federal Aviation Administration [Docket No. FAA–2012–0637; Directorate Identifier 2012–NM–006–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. This proposed AD was prompted by a report of an inboard main landing gear (MLG) door assembly departure due to premature fatigue cracking in the inboard MLG door hinge fittings. This proposed AD would require repetitive inspections for cracking of the inboard MLG door hinge fittings; and modification of cracked fittings, which would terminate the repetitive inspections. We are proposing this AD to detect and correct fatigue cracking in the inboard MLG door hinge fittings which could result in loss of the MLG door assembly from the airplane; loss of the MLG door assembly could impact the flight control surfaces and result in reduced controllability of the airplane. SUMMARY: We must receive comments on this proposed AD by August 2, 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 https://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; Internet https://www.myboeingfleet.com. You may review copies of the referenced DATES: PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 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 https:// 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: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6440; fax: 425–917–6590; email: nancy.marsh@faa.gov. 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– 2012–0637; Directorate Identifier 2012– NM–006–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 https:// 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 received a report of an inboard MLG door assembly departure due to premature fatigue cracking in the inboard MLG door hinge fittings. Fatigue cracking in the inboard MLG door hinge fittings could result in loss of the MLG door assembly from the airplane; such loss could impact the flight control surfaces and result in reduced controllability of the airplane. E:\FR\FM\18JNP1.SGM 18JNP1 36223 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules Relevant Service Information We reviewed Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. The service information describes procedures for doing repetitive detailed or surface high frequency eddy current (HFEC) inspections for cracking of the inboard MLG door hinge fittings; and modification of fittings, which would eliminate the need for the repetitive inspections. The modification consists of replacing the hinge fitting assembly. The initial compliance time is before 10,000 total flight cycles, within 10,000 flight cycles since replacement, or within 600 flight cycles after the effective date of this AD, whichever occurs latest. The repetitive interval is 600 flight cycles or 5,500 flight cycles depending on inspection type. develop in other products of the same type design. FAA’s Determination Costs of Compliance We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or We estimate that this proposed AD affects 1,175 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. ESTIMATED COSTS Action Labor cost Parts cost Cost per product Inspection ......... 3 work-hours × $85 per hour = $255 per inspection cycle. $0 $255 per inspection cycle ............. We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of Cost on U.S. operators $299,625 per inspection cycle. determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Optional Terminating Modification ............................ 9 work-hours × $85 per hour = $765 ....................... According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. TKELLEY on DSK3SPTVN1PROD with PROPOSALS 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 products identified in this rulemaking action. VerDate Mar<15>2010 16:48 Jun 15, 2012 Jkt 226001 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. Accordingly, under the authority delegated to me by the Administrator, Frm 00030 Fmt 4702 Sfmt 4702 Cost per product $6,550 $7,315 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA– 2012–0637; Directorate Identifier 2012– NM–006–AD. (a) Comments Due Date We must receive comments by August 2, 2012. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. (d) Subject The Proposed Amendment PO 00000 Parts cost Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 52, Doors. E:\FR\FM\18JNP1.SGM 18JNP1 36224 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Proposed Rules (e) Unsafe Condition This AD was prompted by a report of an inboard main landing gear (MLG) door assembly departure due to premature fatigue cracking in the inboard MLG door hinge fittings. We are issuing this AD to detect and correct fatigue cracking in the inboard MLG door hinge fittings, which could result in loss of the MLG door assembly from the airplane; loss of the MLG door assembly could impact the flight control surfaces and result in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Initial and Repetitive Inspections Except as provided by paragraph (h) of this AD, at the applicable time in paragraph 1.E. of Boeing Alert Service Bulletin 737– 52A1167, dated December 1, 2011, do either a detailed or surface high frequency eddy current (HFEC) inspection for cracking of the left- and right-side inboard MLG door hinge fittings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. If any cracking is found, before further flight, modify the inboard MLG door hinge fittings on both left- and right-side inboard MLG doors, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. Repeat either inspection at the applicable time in paragraph 1.E. of Boeing Alert Service Bulletin 737–52A1167, dated December 1, 2011. Doing the modification terminates the inspection requirements of this AD. TKELLEY on DSK3SPTVN1PROD with PROPOSALS (h) Exception Where Boeing Alert Service Bulletin 737– 52A1167, dated December 1, 2011, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (i) 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: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has VerDate Mar<15>2010 16:48 Jun 15, 2012 Jkt 226001 been authorized by the Manager, Seattle ACO to make those findings. 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) Related Information (1) For more information about this AD, contact Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: 425–917–6440; fax: 425–917– 6590; email: nancy.marsh@faa.gov. (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; 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. Issued in Renton, Washington, on June 8, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–14806 Filed 6–15–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0638; Directorate Identifier 2011–NM–266–AD] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135 airplanes, and Model EMB–145, –145ER, –145MR, –145LR, –145MP, and –145EP airplanes. This proposed AD was prompted by a report of a lightning strike hitting an airplane tail boom causing certain rear bulkhead parts to jam an elevator control rod. This proposed AD would require installing or reworking, as applicable, metallic diverters and aluminum sheets; modifying the lights assembly on the tail boom rear movable fairing; and replacing the hood assembly with a new hood assembly and SUMMARY: PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 rerouting its electrical harness. We are proposing this AD to prevent lightning strikes from causing certain parts to contact the airplane pitch control system, which could reduce airplane controllability. We must receive comments on this proposed AD by August 2, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro Faria ˜ Lima, 2170—Putim—12227–901 Sao Jose dos Campos—SP—BRASIL; telephone +55 12 3927–5852 or +55 12 3309–0732; fax +55 12 3927–7546; email distrib@embraer.com.br; Internet: https://www.flyembraer.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. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: E:\FR\FM\18JNP1.SGM 18JNP1

Agencies

[Federal Register Volume 77, Number 117 (Monday, June 18, 2012)]
[Proposed Rules]
[Pages 36222-36224]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14806]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0637; Directorate Identifier 2012-NM-006-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and 
-900ER series airplanes. This proposed AD was prompted by a report of 
an inboard main landing gear (MLG) door assembly departure due to 
premature fatigue cracking in the inboard MLG door hinge fittings. This 
proposed AD would require repetitive inspections for cracking of the 
inboard MLG door hinge fittings; and modification of cracked fittings, 
which would terminate the repetitive inspections. We are proposing this 
AD to detect and correct fatigue cracking in the inboard MLG door hinge 
fittings which could result in loss of the MLG door assembly from the 
airplane; loss of the MLG door assembly could impact the flight control 
surfaces and result in reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by August 2, 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 https://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; 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 https://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: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6440; fax: 425-917-6590; email: nancy.marsh@faa.gov.

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-2012-0637; 
Directorate Identifier 2012-NM-006-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 https://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 received a report of an inboard MLG door assembly departure due 
to premature fatigue cracking in the inboard MLG door hinge fittings. 
Fatigue cracking in the inboard MLG door hinge fittings could result in 
loss of the MLG door assembly from the airplane; such loss could impact 
the flight control surfaces and result in reduced controllability of 
the airplane.

[[Page 36223]]

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 737-52A1167, dated 
December 1, 2011. The service information describes procedures for 
doing repetitive detailed or surface high frequency eddy current (HFEC) 
inspections for cracking of the inboard MLG door hinge fittings; and 
modification of fittings, which would eliminate the need for the 
repetitive inspections. The modification consists of replacing the 
hinge fitting assembly. The initial compliance time is before 10,000 
total flight cycles, within 10,000 flight cycles since replacement, or 
within 600 flight cycles after the effective date of this AD, whichever 
occurs latest. The repetitive interval is 600 flight cycles or 5,500 
flight cycles depending on inspection type.

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 the same type design.

Proposed AD Requirements

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

Costs of Compliance

    We estimate that this proposed AD affects 1,175 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
          Action                  Labor cost          Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection................  3 work-hours x $85                 $0   $255 per inspection    $299,625 per
                             per hour = $255 per                     cycle.                 inspection cycle.
                             inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
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 replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                   Action                               Labor cost               Parts cost     Cost per product
----------------------------------------------------------------------------------------------------------------
Optional Terminating Modification...........  9 work-hours x $85 per hour =             $6,550            $7,315
                                               $765.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 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-2012-0637; Directorate Identifier 
2012-NM-006-AD.

(a) Comments Due Date

    We must receive comments by August 2, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes; certificated in any 
category; as identified in Boeing Alert Service Bulletin 737-
52A1167, dated December 1, 2011.

(d) Subject

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

[[Page 36224]]

(e) Unsafe Condition

    This AD was prompted by a report of an inboard main landing gear 
(MLG) door assembly departure due to premature fatigue cracking in 
the inboard MLG door hinge fittings. We are issuing this AD to 
detect and correct fatigue cracking in the inboard MLG door hinge 
fittings, which could result in loss of the MLG door assembly from 
the airplane; loss of the MLG door assembly could impact the flight 
control surfaces and result in reduced controllability of the 
airplane.

(f) Compliance

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

(g) Initial and Repetitive Inspections

    Except as provided by paragraph (h) of this AD, at the 
applicable time in paragraph 1.E. of Boeing Alert Service Bulletin 
737-52A1167, dated December 1, 2011, do either a detailed or surface 
high frequency eddy current (HFEC) inspection for cracking of the 
left- and right-side inboard MLG door hinge fittings, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-52A1167, dated December 1, 2011. If any cracking is 
found, before further flight, modify the inboard MLG door hinge 
fittings on both left- and right-side inboard MLG doors, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-52A1167, dated December 1, 2011. Repeat either 
inspection at the applicable time in paragraph 1.E. of Boeing Alert 
Service Bulletin 737-52A1167, dated December 1, 2011. Doing the 
modification terminates the inspection requirements of this AD.

(h) Exception

    Where Boeing Alert Service Bulletin 737-52A1167, dated December 
1, 2011, specifies a compliance time ``after the original issue date 
of this service bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.

(i) 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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO to make 
those findings. 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) Related Information

    (1) For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6440; fax: 425-917-6590; email: 
nancy.marsh@faa.gov.
    (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; 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.

    Issued in Renton, Washington, on June 8, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-14806 Filed 6-15-12; 8:45 am]
BILLING CODE 4910-13-P
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