8568 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–0242; 

Directorate Identifier 2014–NM–100–AD. 

(a) Comments Due Date 

We must receive comments by April 6, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category. 

(1) Model A300 B4–603, B4–605R, B4–620, 

B4–622, and B4–622R airplanes, all 

manufacturer serial numbers. 

(2) Model A300 C4–605R Variant F 

airplanes, all manufacturer serial numbers. 

(3) Model A300F4–605R airplanes, all 

manufacturer serial numbers, except those on 

which Airbus Modification 12699 was 

embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by the 

manufacturer’s review of all repairs 

accomplished using the structural repair 

manual. This review was done using revised 

fatigue and damage tolerance calculations. 

We are issuing this AD to detect and correct 

previous incomplete or inadequate repairs to 

the surrounding panels of the left and right 

forward passenger doors and the fail-safe 

ring, which could negatively affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the time specified in paragraph (g)(1) or 

(g)(2) of this AD, whichever is later: Do a 

detailed inspection of the surrounding panels 

of the left and right forward passenger doors 

to determine if any repairs have been done, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014. 

(1) Prior to the accumulation of 30,000 

total flight cycles or 67,500 total flight hours, 

whichever occurs first. 

(2) Within 28 months after the effective 

date of this AD. 

(h) Identification of Repairs 

If any affected repair is found during the 

inspection required by paragraph (g) of this 

AD: Before further flight, identify the 

reworked area(s), the percentage of the 

rework, and the limits of the rework, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014. 

(i) Corrective Actions 

During the repair identification required by 

paragraph (h) of this AD, if any rework is 

found that is outside the allowable damage 

limits specified in Airbus Service Bulletin 

A300–53–6173, Revision 01, dated February 

28, 2014: Before further flight, rework or 

repair, as applicable, using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

(j) Exception to Service Information 

Specifications 

Although Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014, specifies to contact Airbus for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; EASA; or 

Airbus’s EASA DOA. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A300–53–6173, 

dated August 1, 2013, which is not 

incorporated by reference in this AD. 

(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. 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. 

(2) Required for Compliance (RC): Except 

as required by paragraph (j) of this AD, if the 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and tests that 

are not identified as RC are recommended. 

Those procedures and tests that are not 

identified 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 procedures and tests 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to procedures 

or tests identified as RC require approval of 

an AMOC. 

(3) 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; 

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) EASA 

Airworthiness Directive 2014–0101, dated 

May 2, 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– 

2015–0242. 

(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 February 

2, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02920 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0245; Directorate 

Identifier 2014–NM–135–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 8569 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2012–24– 

10, which applies to certain The Boeing 

Company Model 747–400 and -400F 

series airplanes. AD 2012–24–10 

currently requires installing new 

software, replacing the duct assembly 

with a new duct assembly, making 

wiring changes, and routing certain wire 

bundles. Since we issued AD 2012–24– 

10, we have received new reports of 

intermittent or blank displays of a 

certain integrated display unit (IDU) 

that were due to an intermittent false 

ground not addressed by the software 

installation or wiring changes required 

by AD 2012–24–10. This proposed AD 

would retain the requirements of AD 

2012–24–10 and would require 

installing a new or serviceable pressure 

switch bracket and altitude pressure 

switch, and add an airplane to the 

applicability of the existing AD. We are 

proposing this AD to prevent IDU 

malfunctions, which could affect the 

ability of the flightcrew to read primary 

displays for airplane attitude, altitude, 

or airspeed, and consequently reduce 

the ability of the flightcrew to maintain 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 6, 2015. 

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– 

0245. 

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– 

0245; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Ana 

Martinez Hueto, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6592; 

fax: 425–917–6591; email: 

ana.m.hueto@faa.gov. 

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–2015–0245; Directorate Identifier 

2014–NM–135–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 

On November 30, 2012, we issued AD 

2012–24–10, Amendment 39–17280 (77 

FR 73908, December 12, 2012), for 

certain The Boeing Company Model 

747–400 and -400F series airplanes. AD 

2012–24–10 requires installing new 

software, replacing the duct assembly 

with a new duct assembly, making 

wiring changes, and routing certain wire 

bundles. AD 2012–24–10 resulted from 

multiple reports of integrated display 

unit (IDU) malfunctions and mode 

control panel (MCP) malfunctions. We 

issued AD 2012–24–10 to prevent IDU 

malfunctions, which could affect the 

ability of the flightcrew to read primary 

displays for airplane attitude, altitude, 

or airspeed, and consequently reduce 

the ability of the flightcrew to maintain 

control of the airplane. 

Actions Since AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), Was Issued 

Since we issued AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), we have received 

reports of intermittent or blank displays 

of a certain IDU in the flight deck that 

were due to an intermittent false ground 

not addressed by the software 

installation or wiring changes required 

by AD 2012–24–10. The false ground 

exists on the 25,000 foot altitude analog/ 

discrete signal of the environmental 

control systems miscellaneous card, 

which is a signal that is transmitted to 

the pack temperature controller. This 

false ground creates a potential to 

circumvent the control logic by allowing 

the 3-way valve to switch air sources 

before an aircraft reaches an altitude of 

25,000 feet, defeating the intent of the 

corrective actions of AD 2012–24–10. 

We have determined that the 

installation of a pressure switch bracket 

and an altitude pressure switch is 

needed on the forward side of the 

station 400 bulkhead to achieve an 

adequate level of safety. The installation 

of the altitude pressure switch would 

change the operating logic for the threeway valve, so that the source for 

equipment cooling air is changed as the 

airplane transitions through an altitude 

of 25,000 feet. Since we issued AD 

2012–24–10, Boeing issued Special 

Attention Service Bulletin 747–21– 

2532; and Special Attention Service 

Bulletin 747–21–2533; both dated 

February 13, 2014; which contain 

procedures for installing the pressure 

switch bracket and altitude pressure 

switch discussed previously. 

Since we issued AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), Boeing also issued 

a revision to Boeing Alert Service 

Bulletin 747–21A2523, Revision 1, 

dated October 3, 2011 (which was 

referenced as a source of service 

information in AD 2012–24–10). Boeing 

Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013, was 

issued to correct wiring instructions for 

747–400BCF airplanes that provide 

crew rest heat below a 25,000 foot 

altitude, and to add an airplane 

configuration having variable number 

RT061 as Group 21 to the effectivity. 

The airplane that was added was 

recently converted from a passenger to 

a freighter configuration, which this 

proposed AD addresses. Since this 

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8570 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 

proposed AD adds this new airplane 

group to the applicability, we have 

added paragraph (j) to this proposed 

AD, which provides new compliance 

times for Group 21 airplanes. 

Related Service Information Under 1 

CFR Part 51 

Boeing issued Boeing Alert Service 

Bulletin 747–21A2523, Revision 2, 

dated June 7, 2013. This service 

information describes procedures for 

changing the wiring and operating logic 

of the equipment cooling three-way 

valve and replacing the existing duct 

assembly with a new duct assembly on 

the main distribution manifold of the air 

conditioning system. 

Boeing also issued Boeing Special 

Attention Service Bulletin 747–21– 

2532, dated February 13, 2014. This 

service information describes 

procedures for installing an altitude 

pressure switch on the forward side of 

the station 400 bulkhead for the threeway valve of the equipment cooling 

system. Boeing also issued Boeing 

Special Attention Service Bulletin 747– 

21–2533, dated February 13, 2014. This 

service information describes 

procedures for adding a second altitude 

signal to the switching logic for the 

three-way valve to provide a second, 

independent, altitude signal for the 

equipment cooling system. 

For information on the procedures 

and compliance times, see this service 

information. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

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 retain all of 

the requirements of AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012.) This proposed AD 

would also require installing a pressure 

switch bracket and altitude pressure 

switch, and would add an airplane to 

the applicability. 

Costs of Compliance 

We estimate that this proposed AD 

affects 33 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Duct assembly and replacement wiring 

changes (retained actions from AD 2012– 

24–10, Amendment 39–17280 (77 FR 

73908, December 12, 2012).

44 work-hours × $85 per hour = $3,740 ........ $20,121 $23,861 $787,413 

Software changes (retained actions from AD 

2012–24–10, Amendment 39–17280 (77 

FR 73908, December 12, 2012).

3 work-hours × $85 per hour = $255 ............. 0 255 8,415 

Altitude pressure switch installation (new proposed action).13 work-hours × $85 per hour = $1,105 ........ 5,230 6,335 209,055 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have 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 that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2012–24–10, Amendment 39–17280 (77 

FR 73908, December 12, 2012), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2015–0245; Directorate Identifier 2014– 

NM–135–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by April 6, 2015. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 8571 

(b) Affected ADs 

This AD replaces AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 and –400F series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 21, Air Conditioning; 31, 

Instruments. 

(e) Unsafe Condition 

This AD was prompted by reports of 

intermittent or blank displays of a certain 

integrated display unit (IDU) in the flight 

deck. We are issuing this AD to prevent IDU 

malfunctions, which could affect the ability 

of the flightcrew to read primary displays for 

airplane attitude, altitude, or airspeed, and 

consequently reduce the ability of the 

flightcrew to maintain control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Software Update 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), with revised service 

information. Within 12 months after January 

16, 2013 (the effective date of AD 2012–24– 

10), except as provided by paragraph (j) of 

this AD: Install integrated display system 

software, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–21A2523, Revision 1, 

dated October 3, 2011; or Boeing Alert 

Service Bulletin 747–21A2523, Revision 2, 

dated June 7, 2013. As of the effective date 

of this AD, only Boeing Alert Service Bulletin 

747–21A2523, Revision 2, dated June 7, 

2013, may be used to accomplish the actions 

required by this paragraph. 

Note 1 to paragraph (g) and (j) of this AD: 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 1, dated October 3, 2011; and 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013; refer to 

Boeing Service Bulletin 747–31–2426, dated 

July 29, 2010 (for airplanes with Rolls-Royce 

engines); Boeing Service Bulletin 747–31– 

2427, dated July 29, 2010 (for airplanes with 

General Electric engines); and Boeing Service 

Bulletin 747–31–2428, dated July 29, 2010 

(for airplanes with Pratt & Whitney engines); 

as additional sources of guidance for the 

software installation specified by paragraph 

(g) of this AD. Boeing Service Bulletin 747– 

31–2426, dated July 29, 2010; Boeing Service 

Bulletin 747–31–2427, dated July 29, 2010; 

and Boeing Service Bulletin 747–31–2428, 

dated July 29, 2010; are not incorporated by 

reference in this AD. 

(h) Retained Duct Assembly Replacement 

and Wiring Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), with revised service 

information. Within 60 months after January 

16, 2013 (the effective date of AD 2012–24– 

10), except as provided by paragraph (j) of 

this AD: Replace the duct assembly with a 

new duct assembly, do wiring changes, and 

route certain wire bundles, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 1, dated October 3, 2011; or Boeing 

Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013. As of the 

effective date of this AD, only Boeing Alert 

Service Bulletin 747–21A2523, Revision 2, 

dated June 7, 2013, may be used to 

accomplish the actions required by this 

paragraph. 

(i) New Installation of Pressure Switch 

Bracket and Altitude Pressure Switch 

Within 60 months after the effective date 

of this AD: Install a new or serviceable 

pressure switch bracket and a new or 

serviceable altitude pressure switch on the 

forward side of the station 400 bulkhead, do 

wiring changes, route certain wire bundles, 

install a new hose assembly, and perform a 

leak check and a functional logic test, in 

accordance with the Accomplishment 

Instructions of the service information 

specified in paragraph (i)(1) or (i)(2) of this 

AD, as applicable. 

(1) For Model 747–400F series airplanes: 

Boeing Alert Service Bulletin 747–21–2532, 

dated February 13, 2014. 

(2) For Model 747–400BCF series 

airplanes: Boeing Alert Service Bulletin 747– 

21–2533, dated February 13, 2014. 

(j) Actions for Group 21 Airplanes 

For Group 21 airplanes, as identified in 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013, do the actions 

specified in paragraphs (j)(1) and (j)(2) of this 

AD, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–21A2523, Revision 2, dated June 7, 

2013. 

(1) Within 12 months after the effective 

date of this AD, install integrated display 

system software. 

(2) Within 60 months after the effective 

date of this AD, replace the duct assembly 

with a new duct assembly, do wiring 

changes, and route certain wire bundles. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–21A2523, Revision 1, 

dated October 3, 2011. 

(l) 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 (m)(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 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), are approved as AMOCs 

for the corresponding provisions of 

paragraphs (g) and (h) of this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Ana Martinez Hueto, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6592; fax: 425–917–6591; 

email: ana.m.hueto@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, Washington. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

2, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02925 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0243; Directorate 

Identifier 2014–NM–114–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

mstockstill on DSK4VPTVN1PROD with PROPOSALS