Airworthiness Directives; The Boeing Company Airplanes, 45385-45387 [2014-18465]

Download as PDF Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Proposed Rules DEPARTMENT OF TRANSPORTATION (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4123 ; fax: (816) 329–4090; email: karl.schletzbaum@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. emcdonald on DSK67QTVN1PROD with PROPOSALS this AD, following the accomplishment instructions in Pacific Aerospace Limited Mandatory Service Bulletin PACSB/FU/095, Issue 2, dated May 28, 2014. (1) Within the next 50 hours time-inservice (TIS) after the effective date of this AD, inspect the control column part number (P/N) 08–45031/32 for cracks. (2) If any mechanical damage, deformation, or cracks are found, before further flight, replace the control column with an airworthy control column P/N 08–45031/32. (3) If no mechanical damage, deformation, or cracks are found after the inspection required in paragraph (f)(1) of this AD, at the next scheduled maintenance inspection or within the next 150 hours TIS, whichever occurs later, replace the control column with an airworthy P/N 08–45031/32. SUMMARY: (h) Related Information Refer to MCAI Civil Aviation Authority (CAA) AD DCA/FU24/183, dated May 29, 2014, and Pacific Aerospace Limited Mandatory Service Bulletin PACSB/FU/095, Issue 2, dated May 28, 2014, for related information. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2014–0532. For service information related to this AD, contact Pacific Aerospace Limited, Airport Road, Hamilton Private Bag 3027 Hamilton 3240, New Zealand; telephone: +64 7 843 6144; fax: +64 7 843 6134; email: pacific@aerospace.co.nz; Internet: https:// www.aerospace.co.nz/. You may review this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on July 29, 2014. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–18449 Filed 8–4–14; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 17:23 Aug 04, 2014 Jkt 232001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0522; Directorate Identifier 2014–NM–087–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 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. This proposed AD was prompted by reports of cracks at the lower forward corner of the main entry door (MED) 1 cutout. This proposed AD would require repetitive inspections of the MED door 1 for cracking, and repair if necessary. This proposed AD also provides optional terminating modification; and would require post-repair or post-modification inspections for cracking, and corrective actions if necessary. We are proposing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by September 19, 2014. 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, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at ADDRESSES: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 45385 the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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 by searching for and locating Docket No. FAA–2014– 0522; 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@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– 2014–0522; Directorate Identifier 2014– NM–087–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 have received reports of cracks at the lower forward corner of the MED 1 cutout on two airplanes. A 1.0-inch crack in the skin and bearstrap was found on an airplane with 17,605 total flight cycles. A 5.0-inch crack was found in the skin, skin doubler, and bearstrap on an airplane with 21,759 total flight cycles. In addition, four cracks between 0.18- and 1.85-inch were found on Boeing’s fatigue test airplane E:\FR\FM\05AUP1.SGM 05AUP1 45386 Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Proposed Rules between 40,000 and 52,250 total pressure cycles. The manufacturer’s analysis has determined that the cracking initiates in the skin and can propagate into the bonded doubler and bearstrap. Skin cracks that are not found and repaired can become large and could adversely affect the structural integrity of the airplane. Relevant Service Information We reviewed Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. For information on the procedures and compliance times, see this service information at https:// www.regulations.gov by searching for Docket No. FAA–2014–0522. 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, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ The phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information The service bulletin 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 165 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection (per door) ..... 11 work-hours × $85 per hour = $935 per inspection cycle. Up to 66 work-hours × $85 per hour = $5,610 .... $0 11 work-hours × $85 per hour = $935 per inspection cycle. 0 Optional modification (per door). Post-repair or -modification inspection (per door). We estimate the following costs to do any necessary repair that would be Parts cost Cost per product 0 Cost on U.S. operators $935 per inspection cycle. Up to $5,610 ................. $154,275 per inspection cycle. Up to $925,650. $935 per inspection cycle. $154,275 per inspection cycle. required based on the results of the proposed inspection. We have no way of determining the number of airplanes that might need this repair: ON-CONDITION COSTS Action Labor cost Parts cost Repair (per door) ................. 66 work-hours × $85 per hour = $5,610 ....................... $7,380 or $9,360 ............... emcdonald on DSK67QTVN1PROD 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 VerDate Mar<15>2010 17:23 Aug 04, 2014 Jkt 232001 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), PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Cost per product $12,990 or $14,970. (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: ■ E:\FR\FM\05AUP1.SGM 05AUP1 Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] (i) Post-Repair or Post-Modification Repetitive Inspections and Corrective Actions 2. Amend § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2014–0522; Directorate Identifier 2014– NM–087–AD. (a) Comments Due Date We must receive comments by September 19, 2014. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. emcdonald on DSK67QTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions Except as specified in paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014: Do a detailed inspection and a surface high frequency eddy current inspection for cracking of the applicable main entry door 1; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. Do all applicable corrective actions before further flight. Repeat the inspections of the applicable main entry door 1 thereafter at the intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. Accomplishing the corrective actions required by this paragraph terminates the repetitive inspection requirements of this paragraph. (h) Optional Terminating Action For airplanes on which no crack is found during the initial inspections required by paragraph (g) of this AD: Installing the preventive modification in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, terminates the repetitive 17:23 Aug 04, 2014 Jkt 232001 For airplanes on which the corrective actions required by paragraph (g) of this AD have been done, or airplanes that have installed the preventive modification specified in paragraph (h) of this AD: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, do a detailed inspection for cracking of the applicable main entry door 1; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, except as specified in paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the applicable main entry door 1 thereafter at the intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. (j) Exceptions to Service Information (e) Unsafe Condition This AD was prompted by reports of cracks at the lower forward corner of the main entry door (MED) 1 cutout. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane. VerDate Mar<15>2010 inspections required by paragraph (g) of this AD. (1) Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, 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. (2) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (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 paragraph (l)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 45387 (l) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425– 917–6590; email: Nathan.P.Weigand@ 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, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on July 25, 2014. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–18465 Filed 8–4–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF JUSTICE 28 CFR Parts 0 and 90 [OVW Docket No. 111] RIN 1105–AB43 Grants To Encourage Arrest Policies and Enforcement of Protection Orders Office on Violence Against Women, Justice. ACTION: Proposed rule. AGENCY: This rule proposes to amend the regulations for the Grants To Encourage Arrest Policies and Enforcement of Protection Orders Program (Arrest Program) to incorporate statutory changes, make minor technical corrections, and streamline existing regulations to reduce repetition of statutory language. This rule would also amend the regulations to clarify that existing regulations on grant-related procedures continue to apply to grants made by the Office on Violence Against Women. DATES: Written comments must be submitted on or before October 6, 2014. ADDRESSES: To ensure proper handling of comments, please reference ‘‘Docket No. OVW 111 on all electronic and written correspondence. The Department encourages the electronic submission of all comments through https://www.regulations.gov using the electronic comment form provided on that site. For easy reference, an electronic copy of this document is also SUMMARY: E:\FR\FM\05AUP1.SGM 05AUP1

Agencies

[Federal Register Volume 79, Number 150 (Tuesday, August 5, 2014)]
[Proposed Rules]
[Pages 45385-45387]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-18465]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0522; Directorate Identifier 2014-NM-087-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 747-100, 747-100B, 747-100B SUD, 747-
200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, 
and 747SP series airplanes. This proposed AD was prompted by reports of 
cracks at the lower forward corner of the main entry door (MED) 1 
cutout. This proposed AD would require repetitive inspections of the 
MED door 1 for cracking, and repair if necessary. This proposed AD also 
provides optional terminating modification; and would require post-
repair or post-modification inspections for cracking, and corrective 
actions if necessary. We are proposing this AD to detect and correct 
skin cracking, which can become large and could adversely affect the 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by September 19, 
2014.

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, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. 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 by searching for and locating Docket No. FAA-2014-
0522; 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), 
FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 
fax: 425-917-6590; email: Nathan.P.Weigand@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-2014-0522; 
Directorate Identifier 2014-NM-087-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 have received reports of cracks at the lower forward corner of 
the MED 1 cutout on two airplanes. A 1.0-inch crack in the skin and 
bearstrap was found on an airplane with 17,605 total flight cycles. A 
5.0-inch crack was found in the skin, skin doubler, and bearstrap on an 
airplane with 21,759 total flight cycles. In addition, four cracks 
between 0.18- and 1.85-inch were found on Boeing's fatigue test 
airplane

[[Page 45386]]

between 40,000 and 52,250 total pressure cycles. The manufacturer's 
analysis has determined that the cracking initiates in the skin and can 
propagate into the bonded doubler and bearstrap. Skin cracks that are 
not found and repaired can become large and could adversely affect the 
structural integrity of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-53A2863, dated March 
11, 2014. For information on the procedures and compliance times, see 
this service information at https://www.regulations.gov by searching for 
Docket No. FAA-2014-0522.

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, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.''
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' correct or address any condition found. 
Corrective actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    The service bulletin 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 165 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 (per door)...........  11 work-hours x $85 per            $0  $935 per inspection  $154,275 per
                                   hour = $935 per                        cycle.               inspection cycle.
                                   inspection cycle.
Optional modification (per door)  Up to 66 work[dash]hours            0  Up to $5,610.......  Up to $925,650.
                                   x $85 per hour = $5,610.
Post-repair or -modification      11 work-hours x $85 per             0  $935 per inspection  $154,275 per
 inspection (per door).            hour = $935 per                        cycle.               inspection cycle.
                                   inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Repair (per door)..................  66 work-hours x $85 per      $7,380 or $9,360......  $12,990 or $14,970.
                                      hour = $5,610.
----------------------------------------------------------------------------------------------------------------

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

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


[[Page 45387]]


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


Sec.  39.13  [Amended]

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

The Boeing Company: Docket No. FAA-2014-0522; Directorate Identifier 
2014-NM-087-AD.

(a) Comments Due Date

    We must receive comments by September 19, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 
747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated 
in any category, as identified in Boeing Alert Service Bulletin 747-
53A2863, dated March 11, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracks at the lower forward 
corner of the main entry door (MED) 1 cutout. We are issuing this AD 
to detect and correct skin cracking, which can become large and 
could adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions

    Except as specified in paragraph (j)(1) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014: Do 
a detailed inspection and a surface high frequency eddy current 
inspection for cracking of the applicable main entry door 1; and do 
all applicable corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2863, dated March 11, 2014. Do all applicable corrective actions 
before further flight. Repeat the inspections of the applicable main 
entry door 1 thereafter at the intervals specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, 
dated March 11, 2014. Accomplishing the corrective actions required 
by this paragraph terminates the repetitive inspection requirements 
of this paragraph.

(h) Optional Terminating Action

    For airplanes on which no crack is found during the initial 
inspections required by paragraph (g) of this AD: Installing the 
preventive modification in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2863, dated 
March 11, 2014, terminates the repetitive inspections required by 
paragraph (g) of this AD.

(i) Post-Repair or Post-Modification Repetitive Inspections and 
Corrective Actions

    For airplanes on which the corrective actions required by 
paragraph (g) of this AD have been done, or airplanes that have 
installed the preventive modification specified in paragraph (h) of 
this AD: At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, dated 
March 11, 2014, do a detailed inspection for cracking of the 
applicable main entry door 1; and do all applicable corrective 
actions; in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, 
except as specified in paragraph (j)(2) of this AD. Do all 
applicable corrective actions before further flight. Repeat the 
inspection of the applicable main entry door 1 thereafter at the 
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2863, dated March 11, 2014.

(j) Exceptions to Service Information

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2863, dated March 11, 2014, 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.
    (2) If any cracking is found during any inspection required by 
this AD, and Boeing Alert Service Bulletin 747-53A2863, dated March 
11, 2014, specifies to contact Boeing for appropriate action: Before 
further flight, repair the cracking using a method approved in 
accordance with the procedures specified in paragraph (k) of this 
AD.

(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 paragraph (l)(1) 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.

(l) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft 
Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: 
Nathan.P.Weigand@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, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 25, 2014.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-18465 Filed 8-4-14; 8:45 am]
BILLING CODE 4910-13-P
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