Document ID: FAA-2015-8429-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2016-01-13T05:00Z

[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)]
[Proposed Rules]
[Pages 1577-1579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-33172]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8429; Directorate Identifier 2015-NM-122-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 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 
fatigue cracks in the station 320 crown frame and in window post number 
3. This proposed AD would require repetitive inspections for cracks and 
missing fasteners of the station 320 crown frame, cracks in the web and 
flange surfaces of the forward segment of window post number 3, and 
missing fasteners and cracks of the window upper sill; post-
modification inspections for cracks of the window upper sill; one-time 
fastener rework; and related investigative and corrective actions if 
necessary. We are proposing this AD to detect and correct fatigue 
cracking and missing fasteners of the station 320 crown frame, cracking 
of the window post number 3, and cracking of the window upper sill, 
which could result in an in-flight decompression and a loss of 
structural integrity of the fuselage.

DATES: We must receive comments on this proposed AD by February 29, 
2016.

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, 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8429.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8429; 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: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: Bill.Ashforth@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-2015-8429; 
Directorate Identifier 2015-NM-122-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 fatigue cracks in the station 320 crown 
frame on Model 747-400 series airplanes. Other Model 747 airplanes, 
except Model 747-8F and 747-8 airplanes, are of a similar station 320 
crown frame configuration. Inner chord cracks of 0.03- to 0.22-inch in 
length have been found on 15 airplanes with total flight cycles ranging 
from 11,498 to 31,315. Also, a 1.8-inch crack was found in the outboard 
web of the frame on one airplane with 14,749 total flight cycles.
    Cracks have also been found in window post number 3, which connects 
to the lower end of the inner chord of the station 320 crown frame. 
Cracks of 0.03- to 0.11-inch in length have been found in window post 
number 3 on five airplanes with total flight cycles ranging from 12,329 
to 15,772.
    Additionally, fatigue cracks that had extended to fully sever the 
inner chord and outboard web of the frame were found on the Model 747-
400 fatigue test airplane at 38,333 total pressure cycles, and 
significant cracks were found in both the frame inner chord and 
outboard web at 30,500 total pressure cycles on the Model 747-100SR 
fatigue test airplane.
    Fatigue cracking and missing fasteners of the station 320 crown 
frame, cracking of the window post number 3, and cracking of the window 
upper sill could result in in-flight decompression and a loss of 
structural integrity of the fuselage.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2862, Revision 1, 
dated July 24, 2015. The service information describes procedures for 
inspections and corrective actions for cracks and missing fasteners in 
the inner chord and outboard webs of the station 320 crown frame, in 
the left and right side window post number 3, and in the upper sill 
structure. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
NPRM.

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

[[Page 1578]]

develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions identified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' For information on the procedures and compliance times, 
see this service information at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-8429.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary actions, and (2) further 
investigate the nature of any condition found. Related investigative 
actions in an AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that 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

    Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 
24, 2015, 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.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which steps in the service information are required for 
compliance with an AD. Differentiating these steps from other tasks in 
the service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The steps identified as Required for 
Compliance (RC) in any service information identified previously have a 
direct effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    For service information that contains steps that are labeled as RC, 
the following provisions apply: (1) The steps labeled as RC, including 
substeps under an RC step and any figures identified in an RC step, 
must be done to comply with the AD, and an alternative method of 
compliance (AMOC) is required for any deviations to RC steps, including 
substeps and identified figures; and (2) steps not labeled as RC may be 
deviated from using accepted methods in accordance with the operator's 
maintenance or inspection program without obtaining approval of an 
AMOC, provided the RC steps, including substeps and identified figures, 
can still be done as specified, and the airplane can be put back in an 
airworthy condition.

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
----------------------------------------------------------------------------------------------------------------
Inspections..............  Up to 193 work-hours x                 $0   Up to $16,405 per     Up to $2,706,825
                            $85 per hour = $16,405                      inspection cycle.     per inspection
                            per inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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:

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

[[Page 1579]]

Sec.  39.13  [Amended]

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

The Boeing Company: Docket No. FAA-2015-8429; Directorate Identifier 
2015-NM-122-AD.

(a) Comments Due Date

    We must receive comments by February 29, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to 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-
53A2862, Revision 1, dated July 24, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracks in the station 
320 crown frame in window post number 3. We are issuing this AD to 
detect and correct fatigue cracking and missing fasteners of the 
station 320 crown frame, cracking of the window post number 3, and 
cracking of the window upper sill, which could result in an in-
flight decompression and a loss of structural integrity of the 
fuselage.

(f) Compliance

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

(g) Initial Inspections, Related Investigative Actions, and Corrective 
Actions

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2862, 
Revision 1, dated July 24, 2015, except as provided by paragraphs 
(j)(1) and (j)(2) of this AD: Do the actions specified in paragraphs 
(g)(1) through (g)(5) of this AD; and do all applicable related 
investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2862, Revision 1, dated July 24, 2015, except as required by 
paragraph (j)(3) of this AD. Do all applicable related investigative 
and corrective actions before further flight.
    (1) Do a detailed inspection for cracks and missing fasteners of 
the station 320 crown frame.
    (2) Do a surface high frequency eddy current (HFEC) inspection 
for cracks of the station 320 crown frame.
    (3) Do a surface HFEC inspection for cracks in the web and 
flange surfaces of the forward segment of window post number 3.
    (4) Do a detailed inspection for missing fasteners of the window 
upper sill.
    (5) Do a surface HFEC inspection for cracks of the window upper 
sill.

(h) Repetitive Inspections and Post-Repair Inspections, Related 
Investigative Actions, and Corrective Actions

    Do applicable repetitive post-repair inspections and repeat the 
inspections specified in paragraphs (g)(1) through (g)(5) of this AD 
for cracking in the window upper sill thereafter at the applicable 
compliance time and intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2862, 
Revision 1, dated July 24, 2015; and do all applicable related 
investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2862, Revision 1, dated July 24, 2015, except as required by 
paragraph (j)(3) of this AD. Do all applicable related investigative 
and corrective actions before further flight.

(i) Fastener Rework, Related Investigative Actions, and Corrective 
Actions

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2862, 
Revision 1, dated July 24, 2015: Do the applicable actions 
(including fastener rework and a detailed inspection of the 
condition of the fastener hole) specified in Part 11 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2862, Revision 1, dated July 24, 2015; and do all applicable 
related investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2862, Revision 1, dated July 24, 2015. Do all applicable related 
investigative and corrective actions before further flight.

(j) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 747-53A2862, Revision 1, 
dated July 24, 2015, specifies a compliance time ``after the 
original date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where Boeing Alert Service Bulletin 747-53A2862, Revision 1, 
dated July 24, 2015, specifies a compliance time ``after the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (3) Where Boeing Alert Service Bulletin 747-53A2862, Revision 1, 
dated July 24, 2015, specifies to contact Boeing for repairs: Before 
further flight, repair, 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, modification, or alteration required by this AD 
if it is approved the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, to make those findings. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) Except as required by paragraphs (g), (h), and (j)(3) of 
this AD: For service information that contains steps that are 
labeled as Required for Compliance (RC), the provisions of 
paragraphs (k)(4)(i) and (k)(4)(ii) apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(l) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-917-6590; email: 
Bill.Ashforth@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 December 23, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-33172 Filed 1-12-16; 8:45 am]
BILLING CODE 4910-13-P