80 FR 72395 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 223 (November 19, 2015)

Page Range		72395-72398
FR Document		2015-29443
We propose to supersede Airworthiness Directive (AD) 95-18-08, for all Airbus Model A300-600 series airplanes. AD 95-18-08 currently requires repetitive inspections to detect cracks in the bottom skin of the wing in the area of the cut out for the pylon rear attachment fitting, and repair if necessary. Since we issued AD 95-18-08, we received a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. This proposed AD would, for certain airplanes, reduce the compliance times for the inspections. We are proposing this AD to detect and correct such fatigue-related cracking, which could result in reduced structural integrity of the wing.
Federal Register, Volume 80 Issue 223 (Thursday, November 19, 2015)
[Federal Register Volume 80, Number 223 (Thursday, November 19, 2015)]
[Proposed Rules]
[Pages 72395-72398]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-29443]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4817; Directorate Identifier 2014-NM-115-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 95-18-08, 
for all Airbus Model A300-600 series airplanes. AD 95-18-08 currently 
requires repetitive inspections to detect cracks in the bottom skin of 
the wing in the area of the cut out for the pylon rear attachment 
fitting, and repair if necessary. Since we issued AD 95-18-08, we 
received a report that updated fatigue and damage tolerance analyses 
and a fleet survey found that certain inspection thresholds and 
intervals must be reduced to allow more timely findings of cracking. 
This proposed AD would, for certain airplanes, reduce the compliance 
times for the inspections. We are proposing this AD to detect and 
correct such fatigue-related cracking, which could result in reduced 
structural integrity of the wing.

DATES: We must receive comments on this proposed AD by January 4, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

[[Page 72396]]

     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 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.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 http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4817; 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 
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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-4817; 
Directorate Identifier 2014-NM-115-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 based on 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

    On August 29, 1995, we issued AD 95-18-08, Amendment 39-9355 (60 FR 
47677, September 14, 1995). AD 95-18-08 requires actions intended to 
address an unsafe condition on all Airbus Model A300-600 series 
airplanes (which includes Airbus Model A300 C4-605R Variant F 
airplanes, Model A300 B4-622 airplanes, and Model A300 F4-622R 
airplanes that were added to the U.S. Type Certificate Data Sheet since 
issuance of AD 95-18-08).
    Since we issued AD 95-18-08, Amendment 39-9355 (60 FR 47677, 
September 14, 1995), we received a report that updated fatigue and 
damage tolerance analyses and a fleet survey done to support a second 
extended service goal for Model A300-600 series airplanes found that 
certain inspection thresholds and intervals must be reduced to allow 
more timely findings of cracking.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0119, dated May 13, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes). The MCAI states:

    Full-scale fatigue tests carried out on the A300-600 test 
specimen by Airbus revealed crack initiation in the bottom skin 
adjacent to the aft pylon attachment fitting.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 94-
069-158(B) (http://ad.easa.europa.eu/blob/1994069158tb_superseded.pdf/AD_F-1994-069-158_2) [which corresponds 
to FAA AD 95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 
1995)] to require repetitive detailed visual inspections (DVI) of 
the wing bottom skin in the area of the cut-out for the pylon rear 
attachment fitting on Left Hand (LH) and Right Hand (RH) wings [to 
detect cracks, and repair if necessary].
    Since that [DGAC] AD was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analyses have been performed in order 
to substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. As a result, it was revealed that the inspection threshold 
and interval must be reduced to allow timely detection of cracks and 
the accomplishment of an applicable corrective action. Prompted by 
these findings, Airbus issued Revision 07 of Service Bulletin (SB) 
A300-57-6028.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 94-069-158(B), which is superseded, 
but reduces the inspection thresholds and intervals [e.g., 
compliance times].

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4817.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A300-57-6028, Revision 07, 
dated June 6, 2011. The service information describes procedures for 
inspections to detect cracks in the bottom skin of the wing in the area 
of the cut out for the pylon rear attachment fitting, and repair. 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 and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 124 airplanes of U.S. 
registry.
    The actions that are required by AD 95-18-08, Amendment 39-9355 (60 
FR 47677, September 14, 1995), and retained in this proposed AD take 
about 6 work-hours per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that are required by AD 95-18-08 is $510 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 15 work-hours and require parts costing $10,000, for a cost 
of $11,275 per product. We have no way of

[[Page 72397]]

determining the number of aircraft that might need these actions.
    The new requirements of this proposed AD add no additional economic 
burden.

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.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-4817; Directorate Identifier 2014-NM-
115-AD.

(a) Comments Due Date

    We must receive comments by January 4, 2016.

(b) Affected ADs

    This AD replaces AD 95-18-08, Amendment 39-9355 (60 FR 47677, 
September 14, 1995).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a report that updated fatigue and damage 
tolerance analyses and a fleet survey found that certain inspection 
thresholds and intervals must be reduced to allow more timely 
findings of cracking. We are issuing this AD to detect and correct 
such fatigue-related cracking, which could result in reduced 
structural integrity of the wing.

(f) Compliance

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

(g) Retained Inspection and Corrective Action With Additional Repair 
Information

    This paragraph restates the requirements of paragraph (a) of AD 
95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995), with 
additional repair contact information. Prior to the accumulation of 
24,000 total flight cycles since date of manufacture of the 
airplane, or within 750 flight cycles after October 16, 1995 (the 
effective date of AD 95-18-08), whichever occurs later, perform a 
detailed visual inspection to detect cracks in the bottom skin of 
the wing in the area of the cut out for the pylon rear attachment 
fitting, in accordance with Airbus Service Bulletin A300-57-6028, 
Revision 3, dated September 13, 1994. Repeat the inspection 
thereafter at intervals not to exceed 9,000 flight cycles. If any 
crack is detected, prior to further flight, repair the wing bottom 
skin in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate, or the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). 
Accomplishing any inspection required by paragraph (h) of this AD 
terminates the inspections required by this paragraph.

(h) New Requirement of This AD: Revised Inspection Thresholds and 
Intervals

    Within the applicable compliance times required in paragraphs 
(h)(1) and (h)(2) of this AD, do a detailed visual inspection of the 
wing bottom skin in the area of the cut-out for the pylon rear 
attachment fitting on left-hand and right-hand wings, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-57-6028, Revision 07, dated June 6, 2011. Repeat the 
inspections thereafter at the applicable intervals required in 
paragraphs (h)(3) and (h)(4) of this AD. Accomplishing any 
inspection required by this paragraph terminates the inspections 
required by paragraph (g) of this AD.
    (1) For ``normal range operations'' airplanes having an average 
flight time of 1.5 flight hours or more: Do the inspection at the 
applicable time required in paragraphs (h)(1)(i) and (h)(1)(ii) of 
this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Do the 
inspection at the later of the times specified in paragraphs 
(h)(1)(i)(A) and (h)(1)(i)(B) of this AD.
    (A) Within 24,000 flight cycles or 51,800 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 2,000 flight cycles or 4,300 flight hours after the 
effective date of this AD, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Do the inspection at the later of the times 
specified in paragraphs (h)(1)(ii)(A) and (h)(1)(ii)(B) of this AD.
    (A) Within 19,100 flight cycles or 41,200 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 1,500 flight cycles or 3,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For ``short range operations'' airplanes having an average 
flight time of less than 1.5 flight hours: Do the inspection at the 
applicable time required in paragraphs (h)(2)(i) and (h)(2)(ii) of 
this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Do the 
inspection at the later of the times specified in paragraphs 
(h)(2)(i)(A) and (h)(2)(i)(B) of this AD.
    (A) Within 25,900 flight cycles or 38,800 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 2,100 flight cycles or 3,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Do

[[Page 72398]]

the inspection at the later of the times specified in paragraphs 
(h)(2)(ii)(A) and (h)(2)(ii)(B) of this AD.
    (A) Within 20,600 flight cycles or 30,900 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 1,600 flight cycles or 2,400 flight hours after the 
effective date of this AD, whichever occurs first.
    (3) For ``normal range operations'' airplanes having an average 
flight time of 1.5 flight hours or more: Repeat the inspection at 
the applicable time required in paragraphs (h)(3)(i) and (h)(3)(ii) 
of this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Repeat the 
inspection thereafter at intervals not to exceed 9,000 flight cycles 
or 19,400 flight hours, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Repeat the inspection thereafter at intervals 
not to exceed 7,100 flight cycles or 15,300 flight hours, whichever 
occurs first.
    (4) For ``short range operations'' airplanes having an average 
flight time of less than 1.5 flight hours: Repeat the inspection at 
the applicable time required in paragraphs (h)(4)(i) and (h)(4)(ii) 
of this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Repeat the 
inspection thereafter at intervals not to exceed 9,700 flight cycles 
or 14,500 flight hours, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Repeat the inspection thereafter at intervals 
not to exceed 7,600 flight cycles or 11,500 flight hours, whichever 
occurs first.

(i) Definition of Average Flight Time for Paragraph (h) of This AD

    For the purpose of paragraph (h) of this AD, the Average Flight 
Time must be established as follows:
    (1) For the initial inspection, the average flight time is the 
total accumulated flight hours, counted from take-off to touch-down, 
divided by the total accumulated flight cycles at the effective date 
of this AD.
    (2) For the first repeated inspection interval, the average 
flight time is the total accumulated flight hours divided by the 
total accumulated flight cycles at the time of the inspection 
threshold.
    (3) For all inspection intervals onwards, the average flight 
time is the flight hours divided by the flight cycles accumulated 
between the last two inspections.

(j) New Requirement of This AD: Corrective Action for Any Cracking 
Found

    If any crack is found during any inspection required by 
paragraph (h) of this AD: Before further flight, repair using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. 
Accomplishing a repair does not constitute terminating action for 
the repetitive inspections required by paragraph (h) of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for inspections required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using any of the service information 
identified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD, 
which are not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A300-57-6028, Revision 04, dated 
October 25, 1999.
    (2) Airbus Service Bulletin A300-57-6028, Revision 05, dated 
January 11, 2002.
    (3) Airbus Service Bulletin A300-57-6028, Revision 06, dated May 
17, 2006.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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. The AMOC approval letter must specifically 
reference this AD.
    (ii) AMOCs approved previously for AD 95-18-08, Amendment 39-
9355 (60 FR 47677, September 14, 1995), are approved as AMOCs for 
the corresponding provisions of paragraph (g) of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2014-
0119, dated May 13, 2014, for related information. This MCAI may be 
found in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2015-4817.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com. You may view this 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 November 11, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-29443 Filed 11-18-15; 8:45 am]
BILLING CODE 4910-13-P
Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 72395

§ 39.13 [Amended] (h) Seal Floor Panels and Seat Tracks/Install Aircraft Certification Office (ACO), 1601 Lind
Drip Shields and Reroute Wiring Avenue SW., Renton, WA 98057–3356;
■ 2. The FAA amends § 39.13 by adding phone: 425–917–6457; fax: 425–917–6590;
Within 60 months after the effective date
the following new airworthiness email: susan.l.monroe@faa.gov.
of this AD: Do the actions specified in
directive (AD): paragraphs (h)(1) and (h)(2) of this AD. (2) For service information identified in
(1) Apply sealant to the main cabin floor this AD, contact Boeing Commercial
The Boeing Company: Docket No. FAA–
areas located above the aft EE bay, in Airplanes, Attention: Data & Services
2015–5808; Directorate Identifier 2015– Management, P.O. Box 3707, MC 2H–65,
NM–111–AD. accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin Seattle, WA 98124–2207; telephone 206–
(a) Comments Due Date 544–5000, extension 1; fax 206–766–5680;
B787–81205–SB530029–00, Issue 001, dated
Internet https://www.myboeingfleet.com. You
We must receive comments by January 4, March 26, 2015.
may view this referenced service information
2016. (2) Install drip shields and foam blocks,
at the FAA, Transport Airplane Directorate,
and reroute the wire bundles above the
(b) Affected ADs 1601 Lind Avenue SW., Renton, WA. For
equipment in the aft EE bay, in accordance
information on the availability of this
None. with the Accomplishment Instructions of
material at the FAA, call 425–227–1221.
Boeing Alert Service Bulletin B787–81205–
(c) Applicability SB530031–00, Issue 001, dated March 26, Issued in Renton, Washington, on
This AD applies to The Boeing Company 2015. November 9, 2015.
Model 787–8 series airplanes, certificated in (i) Alternative Methods of Compliance Michael Kaszycki,
any category, as identified in the service (AMOCs) Acting Manager, Transport Airplane
information specified in paragraphs (c)(1), Directorate, Aircraft Certification Service.
(1) The Manager, Seattle Aircraft
(c)(2), and (c)(3) of this AD. Certification Office (ACO), FAA, has the [FR Doc. 2015–29441 Filed 11–18–15; 8:45 am]
(1) Boeing Alert Service Bulletin B787– authority to approve AMOCs for this AD, if BILLING CODE 4910–13–P
81205–SB380009–00, Issue 001, dated March requested using the procedures found in 14
26, 2015. CFR 39.19. In accordance with 14 CFR 39.19,
(2) Boeing Alert Service Bulletin B787– send your request to your principal inspector DEPARTMENT OF TRANSPORTATION
81205–SB530029–00, Issue 001, dated March or local Flight Standards District Office, as
26, 2015. appropriate. If sending information directly Federal Aviation Administration
(3) Boeing Alert Service Bulletin B787– to the manager of the ACO, send it to the
81205–SB530031–00, Issue 001, dated March attention of the person identified in 14 CFR Part 39
26, 2015. paragraph (j)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOC- [Docket No. FAA–2015–4817; Directorate
(d) Subject Requests@faa.gov. Identifier 2014–NM–115–AD]
Air Transport Association (ATA) of (2) Before using any approved AMOC,
America Code 38, Water/Waste; and Code 53, notify your appropriate principal inspector, RIN 2120–AA64
Fuselage. or lacking a principal inspector, the manager
of the local flight standards district office/ Airworthiness Directives; Airbus
(e) Unsafe Condition certificate holding district office. Airplanes
This proposed AD was prompted by (3) An AMOC that provides an acceptable AGENCY: Federal Aviation
reports of water leakage from the potable level of safety may be used for any repair,
alteration, or modification required by this
Administration (FAA), DOT.
water system due to improperly installed
waterline couplings, and water leaking into AD if it is approved by the Boeing ACTION: Notice of proposed rulemaking
the electronics equipment (EE) bays from Commercial Airplanes Organization (NPRM).
above the floor in the main cabin, resulting Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO SUMMARY: We propose to supersede
in water on the equipment in the EE bays. We
are issuing this AD to prevent a water leak to make those findings. For a repair method Airworthiness Directive (AD) 95–18–08,
from an improperly installed potable water to be approved, the repair method, for all Airbus Model A300–600 series
system coupling, or main cabin water source, modification deviation, or alteration airplanes. AD 95–18–08 currently
which could cause the equipment in the EE deviation must meet the certification basis of requires repetitive inspections to detect
bays to become wet, resulting in an electrical the airplane, and the approval must cracks in the bottom skin of the wing in
short and potential loss of system functions specifically refer to this AD. the area of the cut out for the pylon rear
(4) For service information that contains
essential for safe flight. attachment fitting, and repair if
steps that are labeled as Required for
(f) Compliance Compliance (RC), the provisions of necessary. Since we issued AD 95–18–
paragraphs (i)(4)(i) and (i)(4)(ii) apply. 08, we received a report that updated
Comply with this AD within the fatigue and damage tolerance analyses
compliance times specified, unless already (i) The steps labeled as RC, including
substeps under an RC step and any figures and a fleet survey found that certain
done.
identified in an RC step, must be done to inspection thresholds and intervals
(g) Replace Potable Waterline Couplings comply with the AD. An AMOC is required must be reduced to allow more timely
Within 24 months after the effective date for any deviations to RC steps, including findings of cracking. This proposed AD
substeps and identified figures. would, for certain airplanes, reduce the
of this AD: Replace the existing potable
(ii) Steps not labeled as RC may be
waterline couplings located above the compliance times for the inspections.
deviated from using accepted methods in
forward and aft EE bays with new, improved
accordance with the operator’s maintenance We are proposing this AD to detect and
couplings, in accordance with the or inspection program without obtaining correct such fatigue-related cracking,
Accomplishment Instructions of Boeing Alert approval of an AMOC, provided the RC steps, which could result in reduced structural
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Service Bulletin B787–81205–SB380009–00, including substeps and identified figures, can integrity of the wing.
Issue 001, dated March 26, 2015. Before still be done as specified, and the airplane DATES: We must receive comments on
further flight after doing the replacement, do can be put back in an airworthy condition.
a potable water system leak test and repair
this proposed AD by January 4, 2016.
any leaks found before further flight, in (j) Related Information ADDRESSES: You may send comments by
accordance with the Accomplishment (1) For more information about this AD, any of the following methods:
Instructions of Boeing Alert Service Bulletin contact Susan L. Monroe, Aerospace • Federal eRulemaking Portal: Go to
B787–81205–SB380009–00, Issue 001, dated Engineer, Cabin Safety and Environmental http://www.regulations.gov. Follow the
March 26, 2015. Systems Branch, ANM–150S, FAA, Seattle instructions for submitting comments.

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72396 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules

• Fax: 202–493–2251. We will post all comments we result, it was revealed that the inspection
• Mail: U.S. Department of receive, without change, to http:// threshold and interval must be reduced to
Transportation, Docket Operations, M– www.regulations.gov, including any allow timely detection of cracks and the
30, West Building Ground Floor, Room accomplishment of an applicable corrective
personal information you provide. We
W12–140, 1200 New Jersey Avenue SE., action. Prompted by these findings, Airbus
will also post a report summarizing each issued Revision 07 of Service Bulletin (SB)
Washington, DC 20590. substantive verbal contact we receive A300–57–6028.
• Hand Delivery: U.S. Department of about this proposed AD. For the reasons described above, this
Transportation, Docket Operations, M– [EASA] AD retains the requirements of DGAC
30, West Building Ground Floor, Room Discussion
France AD 94–069–158(B), which is
W12–140, 1200 New Jersey Avenue SE., On August 29, 1995, we issued AD superseded, but reduces the inspection
Washington, DC, between 9 a.m. and 5 95–18–08, Amendment 39–9355 (60 FR thresholds and intervals [e.g., compliance
p.m., Monday through Friday, except 47677, September 14, 1995). AD 95–18– times].
Federal holidays. 08 requires actions intended to address You may examine the MCAI in the
For service information identified in an unsafe condition on all Airbus Model AD docket on the Internet at http://
this proposed AD, contact Airbus SAS, A300–600 series airplanes (which www.regulations.gov by searching for
Airworthiness Office—EAW, 1 Rond includes Airbus Model A300 C4–605R and locating Docket No. FAA–2015–
Point Maurice Bellonte, 31707 Blagnac Variant F airplanes, Model A300 B4–
Cedex, France; telephone +33 5 61 93 36 4817.
622 airplanes, and Model A300 F4–
96; fax +33 5 61 93 44 51; email 622R airplanes that were added to the Related Service Information Under 1
account.airworth-eas@airbus.com; U.S. Type Certificate Data Sheet since CFR Part 51
Internet http://www.airbus.com. You issuance of AD 95–18–08).
may view this referenced service We reviewed Airbus Service Bulletin
Since we issued AD 95–18–08, A300–57–6028, Revision 07, dated June
information at the FAA, Transport Amendment 39–9355 (60 FR 47677,
Airplane Directorate, 1601 Lind Avenue 6, 2011. The service information
September 14, 1995), we received a describes procedures for inspections to
SW., Renton, WA. For information on report that updated fatigue and damage
the availability of this material at the detect cracks in the bottom skin of the
tolerance analyses and a fleet survey wing in the area of the cut out for the
FAA, call 425–227–1221. done to support a second extended pylon rear attachment fitting, and
Examining the AD Docket service goal for Model A300–600 series repair. This service information is
airplanes found that certain inspection reasonably available because the
You may examine the AD docket on thresholds and intervals must be
the Internet at http:// interested parties have access to it
reduced to allow more timely findings through their normal course of business
www.regulations.gov by searching for of cracking.
and locating Docket No. FAA–2015– or by the means identified in the
The European Aviation Safety Agency
4817; or in person at the Docket ADDRESSES section of this NPRM.
(EASA), which is the Technical Agent
Management Facility between 9 a.m. for the Member States of the European FAA’s Determination and Requirements
and 5 p.m., Monday through Friday, Union, has issued EASA Airworthiness of This Proposed AD
except Federal holidays. The AD docket Directive 2014–0119, dated May 13,
contains this proposed AD, the This product has been approved by
2014 (referred to after this as the
regulatory evaluation, any comments the aviation authority of another
Mandatory Continuing Airworthiness
received, and other information. The country, and is approved for operation
Information, or ‘‘the MCAI’’), to correct
street address for the Docket Operations in the United States. Pursuant to our
an unsafe condition on all Airbus Model
office (telephone 800–647–5527) is in bilateral agreement with the State of
A300 B4–600, B4–600R, and F4–600R
the ADDRESSES section. Comments will Design Authority, we have been notified
series airplanes, and Model A300 C4–
be available in the AD docket shortly of the unsafe condition described in the
605R Variant F airplanes (collectively
after receipt. MCAI and service information
called Model A300–600 series
FOR FURTHER INFORMATION CONTACT: Dan referenced above. We are proposing this
airplanes). The MCAI states:
Rodina, Aerospace Engineer, AD because we evaluated all pertinent
International Branch, ANM–116, Full-scale fatigue tests carried out on the information and determined an unsafe
A300–600 test specimen by Airbus revealed condition exists and is likely to exist or
Transport Airplane Directorate, FAA, crack initiation in the bottom skin adjacent
1601 Lind Avenue SW., Renton, WA develop on other products of the same
to the aft pylon attachment fitting.
98057–3356; telephone 425–227–2125; This condition, if not detected and type design.
fax 425–227–1149. corrected, could affect the structural integrity Costs of Compliance
SUPPLEMENTARY INFORMATION: of the aeroplane.
To address this unsafe condition, DGAC We estimate that this proposed AD
Comments Invited [Direction Générale de l’Aviation Civile] affects 124 airplanes of U.S. registry.
We invite you to send any written France issued AD 94–069–158(B) (http:// The actions that are required by AD
ad.easa.europa.eu/blob/1994069158tb_ 95–18–08, Amendment 39–9355 (60 FR
relevant data, views, or arguments about superseded.pdf/AD_F-1994-069-158_2)
this proposed AD. Send your comments [which corresponds to FAA AD 95–18–08, 47677, September 14, 1995), and
to an address listed under the Amendment 39–9355 (60 FR 47677, retained in this proposed AD take about
ADDRESSES section. Include ‘‘Docket No. September 14, 1995)] to require repetitive 6 work-hours per product, at an average
FAA–2015–4817; Directorate Identifier detailed visual inspections (DVI) of the wing labor rate of $85 per work-hour. Based
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2014–NM–115–AD’’ at the beginning of bottom skin in the area of the cut-out for the on these figures, the estimated cost of
your comments. We specifically invite pylon rear attachment fitting on Left Hand the actions that are required by AD 95–
comments on the overall regulatory, (LH) and Right Hand (RH) wings [to detect 18–08 is $510 per product.
cracks, and repair if necessary].
economic, environmental, and energy Since that [DGAC] AD was issued, a fleet
In addition, we estimate that any
aspects of this proposed AD. We will survey and updated Fatigue and Damage necessary follow-on actions would take
consider all comments received by the Tolerance analyses have been performed in about 15 work-hours and require parts
closing date and may amend this order to substantiate the second A300–600 costing $10,000, for a cost of $11,275
proposed AD based on those comments. Extended Service Goal (ESG2) exercise. As a per product. We have no way of

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Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 72397

determining the number of aircraft that PART 39—AIRWORTHINESS 13, 1994. Repeat the inspection thereafter at
might need these actions. DIRECTIVES intervals not to exceed 9,000 flight cycles. If
any crack is detected, prior to further flight,
The new requirements of this repair the wing bottom skin in accordance
proposed AD add no additional ■ 1. The authority citation for part 39
continues to read as follows: with a method approved by the Manager,
economic burden. Standardization Branch, ANM–113, FAA,
Authority: 49 U.S.C. 106(g), 40113, 44701. Transport Airplane Directorate, or the
Authority for This Rulemaking
Manager, International Branch, ANM–116,
§ 39.13 [Amended] Transport Airplane Directorate, FAA; or the
Title 49 of the United States Code
specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by European Aviation Safety Agency (EASA); or
rules on aviation safety. Subtitle I, removing Airworthiness Directive (AD) Airbus’s EASA Design Organization
95–18–08, Amendment 39–9355 (60 FR Approval (DOA). Accomplishing any
section 106, describes the authority of inspection required by paragraph (h) of this
the FAA Administrator. ‘‘Subtitle VII: 47677, September 14, 1995), and adding
the following new AD: AD terminates the inspections required by
Aviation Programs,’’ describes in more this paragraph.
detail the scope of the Agency’s Airbus: Docket No. FAA–2015–4817;
Directorate Identifier 2014–NM–115–AD. (h) New Requirement of This AD: Revised
authority.
Inspection Thresholds and Intervals
We are issuing this rulemaking under (a) Comments Due Date
Within the applicable compliance times
the authority described in ‘‘Subtitle VII, We must receive comments by January 4, required in paragraphs (h)(1) and (h)(2) of
Part A, Subpart III, Section 44701: 2016. this AD, do a detailed visual inspection of
General requirements.’’ Under that the wing bottom skin in the area of the cut-
(b) Affected ADs
section, Congress charges the FAA with out for the pylon rear attachment fitting on
promoting safe flight of civil aircraft in This AD replaces AD 95–18–08, left-hand and right-hand wings, in
Amendment 39–9355 (60 FR 47677,
air commerce by prescribing regulations accordance with the Accomplishment
September 14, 1995). Instructions of Airbus Service Bulletin A300–
for practices, methods, and procedures
the Administrator finds necessary for (c) Applicability 57–6028, Revision 07, dated June 6, 2011.
safety in air commerce. This regulation Repeat the inspections thereafter at the
This AD applies to the airplanes identified
applicable intervals required in paragraphs
is within the scope of that authority in paragraphs (c)(1) through (c)(4) of this AD,
(h)(3) and (h)(4) of this AD. Accomplishing
because it addresses an unsafe condition certificated in any category, all manufacturer
any inspection required by this paragraph
that is likely to exist or develop on serial numbers.
terminates the inspections required by
products identified in this rulemaking (1) Airbus Model A300 B4–601, B4–603,
paragraph (g) of this AD.
B4–620, and B4–622 airplanes.
action. (2) Airbus Model A300 B4–605R and B4–
(1) For ‘‘normal range operations’’
airplanes having an average flight time of 1.5
Regulatory Findings 622R airplanes.
flight hours or more: Do the inspection at the
(3) Airbus Model A300 F4–605R and F4–
We determined that this proposed AD applicable time required in paragraphs
622R airplanes.
(h)(1)(i) and (h)(1)(ii) of this AD.
would not have federalism implications (4) Airbus Model A300 C4–605R Variant F
(i) For Model A300 F4–605R and F4–622R
under Executive Order 13132. This airplanes.
airplanes: Do the inspection at the later of the
proposed AD would not have a (d) Subject times specified in paragraphs (h)(1)(i)(A) and
substantial direct effect on the States, on (h)(1)(i)(B) of this AD.
Air Transport Association (ATA) of
the relationship between the national America Code 57, Wings. (A) Within 24,000 flight cycles or 51,800
Government and the States, or on the flight hours after first flight of the airplane,
distribution of power and (e) Reason whichever occurs first.
responsibilities among the various This AD was prompted by a report that (B) Within 2,000 flight cycles or 4,300
levels of government. updated fatigue and damage tolerance flight hours after the effective date of this AD,
analyses and a fleet survey found that certain whichever occurs first.
For the reasons discussed above, I (ii) For Model A300 B4–600, B4–600R, and
inspection thresholds and intervals must be
certify this proposed regulation: reduced to allow more timely findings of Model A300 C4–605R Variant F airplanes: Do
1. Is not a ‘‘significant regulatory cracking. We are issuing this AD to detect the inspection at the later of the times
action’’ under Executive Order 12866; and correct such fatigue-related cracking, specified in paragraphs (h)(1)(ii)(A) and
2. Is not a ‘‘significant rule’’ under the which could result in reduced structural (h)(1)(ii)(B) of this AD.
integrity of the wing. (A) Within 19,100 flight cycles or 41,200
DOT Regulatory Policies and Procedures
flight hours after first flight of the airplane,
(44 FR 11034, February 26, 1979); (f) Compliance whichever occurs first.
3. Will not affect intrastate aviation in Comply with this AD within the (B) Within 1,500 flight cycles or 3,200
Alaska; and compliance times specified, unless already flight hours after the effective date of this AD,
4. Will not have a significant done. whichever occurs first.
economic impact, positive or negative, (2) For ‘‘short range operations’’ airplanes
(g) Retained Inspection and Corrective having an average flight time of less than 1.5
on a substantial number of small entities Action With Additional Repair Information flight hours: Do the inspection at the
under the criteria of the Regulatory This paragraph restates the requirements of applicable time required in paragraphs
Flexibility Act. paragraph (a) of AD 95–18–08, Amendment (h)(2)(i) and (h)(2)(ii) of this AD.
List of Subjects in 14 CFR Part 39 39–9355 (60 FR 47677, September 14, 1995), (i) For Model A300 F4–605R and F4–622R
with additional repair contact information. airplanes: Do the inspection at the later of the
Air transportation, Aircraft, Aviation Prior to the accumulation of 24,000 total times specified in paragraphs (h)(2)(i)(A) and
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safety, Incorporation by reference, flight cycles since date of manufacture of the (h)(2)(i)(B) of this AD.
Safety. airplane, or within 750 flight cycles after (A) Within 25,900 flight cycles or 38,800
October 16, 1995 (the effective date of AD flight hours after first flight of the airplane,
The Proposed Amendment 95–18–08), whichever occurs later, perform a whichever occurs first.
detailed visual inspection to detect cracks in (B) Within 2,100 flight cycles or 3,200
Accordingly, under the authority the bottom skin of the wing in the area of the flight hours after the effective date of this AD,
delegated to me by the Administrator, cut out for the pylon rear attachment fitting, whichever occurs first.
the FAA proposes to amend 14 CFR part in accordance with Airbus Service Bulletin (ii) For Model A300 B4–600, B4–600R, and
39 as follows: A300–57–6028, Revision 3, dated September Model A300 C4–605R Variant F airplanes: Do

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Document Created: 2015-12-14 13:56:37
Document Modified: 2015-12-14 13:56:37
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by January 4, 2016.
Contact		Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149.
FR Citation		80 FR 72395
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 72395 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 223 (November 19, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
