63080 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Rules and Regulations 

modified FOHE (incorporating enhanced 

anti-icing and de-icing performance) is 

required to be installed on all Trent 700 

engines through EASA AD 2009–0257 

[http://ad.easa.europa.eu/ad/2009-0257] 

[which corresponds to FAA AD 2010–07–01, 

Amendment 39–16244 (75 FR 15326, March 

29, 2010)]. 

Previously, the operation of the WSS at Rib 

3 was no longer considered as a main 

contributory factor on ice build-up and 

subsequent release of ice into the fuel system. 

Based on the latest information, the 

deactivation of the automatic Standby Fuel 

Pump Scavenge System is no longer required. 

For the reasons described above, this 

Notice cancels EASA AD 2010–0132R1. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0656- 

0004. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 59468, October 2, 2014), or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

59468, October 2, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 59468, 

October 2, 2014). 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0656; 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 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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: 

■ (a) Removing Airworthiness Directive 

(AD) 2010–08–08, Amendment 39– 

16263 (75 FR 19196, April 14, 2010); 

and AD 2011–06–04, Amendment 39– 

16628 (76 FR 13075, March 10, 2011), 

and 

■ (b) Adding the following new AD: 

2015–21–03 Airbus: Amendment 39–18295. 

Docket No. FAA–2014–0656; Directorate 

Identifier 2013–NM–224–AD. 

(a) Effective Date 

This AD becomes effective November 23, 

2015. 

(b) Affected ADs 

This AD removes AD 2010–08–08, 

Amendment 39–16263 (75 FR 19196, April 

14, 2010); and AD 2011–06–04, Amendment 

39–16628 (76 FR 13075, March 10, 2011). 

(c) Applicability 

This AD applies to the airplanes specified 

in paragraphs (c)(1) and (c)(2) of this AD. 

(1) Airbus Model A330–243, –341, –342, 

and –343 airplanes, certificated in any 

category, all manufacturer serial numbers 

equipped with Rolls-Royce Trent 700 

engines, on which Airbus Modification 

56966MP16199 has been embodied in 

production or Airbus Service Bulletin A330– 

28–3105 has been embodied in service. 

(2) Airbus Model A330–243F airplanes, 

certificated in any category, all manufacturer 

serial numbers on which Airbus Modification 

56966H16199 has been embodied in 

production or Airbus Service Bulletin A330– 

28–3105 has been embodied in service. 

Issued in Renton, Washington, on October 

6, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26219 Filed 10–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4203; Directorate 

Identifier 2015–NM–142–AD; Amendment 

39–18299; AD 2015–21–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200, A330–200 

Freighter, A330–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. This AD requires a detailed 

inspection of the girt installation of each 

escape slide and slide raft, and 

corrective action if necessary. This AD 

was prompted by a report of incorrect 

installation of the girt panel on 

passenger doors and an incorrectly 

installed quick release (girt) bar into the 


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girt panel of the slide raft. We are 

issuing this AD to detect and correct 

incorrect girt installation of the escape 

slide and slide raft, which could prevent 

slide deployment during an emergency, 

and result in reduced evacuation 

capacity from the airplane and possible 

injury to occupants. 

DATES: This AD becomes effective 

November 3, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 3, 2015. 

We must receive comments on this 

AD by December 3, 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: 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 AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4203. 

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– 

4203; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0183R1, dated 

September 29, 2015 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–200, 

A330–200 Freighter, A330–300, A340– 

200, A340–300, A340–500, and A340– 

600 series airplanes. The MCAI states: 

During inspections of two different A330 

aeroplanes before delivery, incorrect 

connection of the girt panel was noticed on 

one passenger (PAX) door 2 and one PAX 

door 4. Further investigation revealed that 

the quick release (girt) bar was incorrectly 

installed into the girt panel of the affected 

slide raft. 

This condition, if not detected and 

corrected, would cause the slide pack to 

remain attached to the door, preventing slide 

deployment during an emergency (door in 

‘‘ARMED’’ mode), leading to reduced 

evacuation capacity from the aeroplane and 

possible injury to occupants. 

Further inspections at the Airbus final 

assembly line revealed a third case of 

incorrect installation of girt panel, on one 

emergency exit door. 

Prompted by these findings, Airbus issued 

Alert Operators Transmission (AOT) 

A25L004–15 to provide inspection 

instructions. 

For the reasons described above, EASA 

issued AD 2015–0183 to require a one-time 

inspection of the escape slide and slide/raft 

attachments and, depending on findings, 

accomplishment of applicable corrective 

action(s) [including reinstalling the slide or 

declaring the affected door inoperative]. 

Since that AD was issued, it was found that 

the Applicability could be reduced by 

excluding some aeroplanes and that there 

was a need to clarify the applicable Airbus 

MPD Tasks and MRBR MSI. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–4203. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Alert Operators 

Transmission (AOT) A25L004–15, Rev 

00, dated August 24, 2015. The service 

information describes procedures for 

performing a visual inspection of the 

girt installations of each slide and slide 

raft, and corrective action. 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 AD. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because incorrect girt installation of 

the of escape slide and slide raft could 

prevent slide deployment during an 

emergency and result in reduced 

evacuation capacity from the airplane 

and possible injury to occupants. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–4203; 

Directorate Identifier 2015–NM–142– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 


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personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 30 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $0 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $2,550, or $85 

per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 18 work-hours, for a cost of 

$1,530 per escape slide/slide raft. We 

have no way of determining the number 

escape slides/slide rafts on the aircraft 

that might need this action. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2015–21–07 Airbus: Amendment 39–18299. 

Docket No. FAA–2015–4203; Directorate 

Identifier 2015–NM–142–AD. 

(a) Effective Date 

This AD becomes effective November 3, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, as specified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) This AD applies to the airplanes 

identified in paragraphs (c)(1)(i) through 

(c)(1)(vii) of this AD. 

(i) Model A330–201, –202, –203, –223, and 

–243 airplanes. 

(ii) Model A330–223F and –243F airplanes. 

(iii) Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes. 

(iv) Model A340–211, –212, and –213 

airplanes. 

(v) Model A340–311, –312, and –313 

airplanes. 

(vi) Model A340–541 airplanes. 

(vii) Model A340–642 airplanes. 

(2) This AD does not apply to airplanes on 

which the installations of all escape slides 

and slide rafts have passed an inspection as 

specified in any task/item identified in 

paragraphs (c)(2)(i) through (c)(2)(v) of this 

AD. 

(i) Task 25–62–41–01–1 Cabin Escape 

Facilities, of the applicable Airbus 

Maintenance Planning Document. 

(ii) Task 25–62–41–02–1 Cabin Escape 

Facilities, of the applicable Airbus 

Maintenance Planning Document. 

(iii) Task 25–62–41–03–1 Cabin Escape 

Facilities, of the applicable Airbus 

Maintenance Planning Document. 

(iv) Task 25–62–41–04–1 Cabin Escape 

Facilities, of the applicable Airbus 

Maintenance Planning Document. 

(v) Maintenance Schedule Item 25.62.00 

section 01, 02, or 03, of the Cabin Escape 

Facilities, of the applicable Airbus 

Maintenance Review Board Report. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/furnishings. 

(e) Reason 

This AD was prompted by a report of 

incorrect installation of the girt panel on 

passenger doors and an incorrectly installed 

quick release (girt) bar into the girt panel of 

the slide raft. We are issuing this AD to 

detect and correct incorrect girt installation 

of the escape slide and slide raft, which 

could prevent slide deployment during an 

emergency, and result in reduced evacuation 

capacity from the airplane and possible 

injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 30 days after the effective date of 

this AD, inspect to identify the slide raft and 

escape slide part numbers installed on the 

airplane. A review of the airplane delivery or 

maintenance records may be used in lieu of 

the inspection if the slide raft and escape 

slide part numbers can be conclusively 

defined through such review. 

(h) Affected Slides and Slide Rafts 

(1) If the inspection required by paragraph 

(g) of this AD reveals any slide raft having 

P/N 7A1508, 7A1510, 7A1539, or 4A3934 

series, or any escape slide having P/N 

7A1509 or 4A3928 series: Within 30 days 

after the effective date of this AD, do a 

detailed inspection of the girt installation of 

the affected escape slide and slide raft, in 

accordance with paragraph 4.2 of Airbus 

AOT A25L004–15, Rev 00, dated August 24, 

2015. 

(2) For any door position where an affected 

slide raft or escape slide has been removed 

and reinstalled, or replaced since the 

airplane’s entry into service, the inspection 

of the girt installation of the slide raft or 

escape slide at that position, as required by 

paragraph (h)(1) of this AD, does not have to 

be done. 

(i) Corrective Action 

If, during the inspection required by 

paragraph (h)(1) of this AD, the girt bar fitted 

into the girt of an escape slide, or the quick 

release bar fitted into the girt of a slide raft, 

is found to be incorrectly installed, before 

further flight, accomplish the applicable 

corrective action(s), in accordance with 

paragraph 4.3 of Airbus AOT A25L004–15, 

Rev 00, dated August 24, 2015. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 


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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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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) 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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0183, dated 

August 31, 2015, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–4203. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

A25L004–15, Rev 00, dated August 24, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26603 Filed 10–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0277; Directorate 

Identifier 2015–NE–05–AD; Amendment 39– 

18262; AD 2015–18–04] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International S.A. Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to certain CFM International 

S.A. (CFM) CFM56–7B and CFM56–3 

turbofan engines. Four headings in the 

Compliance section are incorrect. This 

document corrects the errors. In all 

other respects, the original document 

remains the same. 

DATES: This final rule is effective on 

October 20, 2015. The effective date of 

AD 2015–18–04, Amendment 39–18262 

(80 FR 55235, September 15, 2015) 

remains October 20, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Kyle 

Gustafson, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7183; fax: 781–238– 

7199; email: kyle.gustafson@faa.gov. 

SUPPLEMENTARY INFORMATION: AD 2015– 

18–04, Amendment 39–18262 (80 FR 

55235, September 15, 2015), requires 

AGB/transfer gearbox (TGB) magnetic 

chip detector (MCD) inspection of the 

affected gearshafts until removal. 

As published, four headings in the 

Compliance section are incorrect. 

No other part of the final rule has 

been changed. 

The effective date of AD 2015–18–04 

remains October 20, 2015. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

■ 2. The FAA republishes airworthiness 

directive (AD) 2015–18–04, Amendment 

39–18262 (80 FR 55235, September 15, 

2015) as follows: 

2015–18–04 CFM International S.A.: 

Amendment 39–18262; Docket No. 

FAA–2015–0277; Directorate Identifier 

2015–NE–05–AD. 

(a) Effective Date 

This AD is effective October 20, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to CFM International S.A. 

(CFM) CFM56–7B and CFM56–3 engines 

with a 73-tooth or 41-tooth gearshaft installed 

in the accessory gearbox (AGB), that has a 

gearshaft serial number in Appendix A or 

Appendix B of CFM Service Bulletin (SB) No. 

CFM56–7B S/B 72–0964, Revision 1, dated 

December 15, 2014. 

(d) Unsafe Condition 

This AD was prompted by a report of an 

uncommanded in-flight shutdown on a CFM 

CFM56–7B engine following rupture of the 

73-tooth gearshaft located in the engine AGB. 

We are issuing this AD to prevent failure of 

certain AGB gearshafts, which could lead to 

failure of one or more engines, loss of thrust 

control, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Initial AGB/Transfer Gearbox (TGB)/

Magnetic Chip Detector (MCD) Inspection 

and Analysis for CFM56–7B Engines 

(i) For affected 73-tooth gearshafts, perform 

an AGB/TGB MCD inspection within 250 

flight hours (FHs) since last inspection, 

within 25 FHs from the effective date of this 

AD, or when the gearshaft accumulates 3,000 

FHs since new, whichever comes later. 

(ii) For affected 41-tooth gearshafts, 

perform an AGB/TGB MCD inspection within 

250 FHs since last inspection, within 25 FHs 

from the effective date of this AD, or when 

the gearshaft accumulates 6,000 FHs since 

new, whichever comes later. 

(iii) If any magnetic particles, including 

fuzz, are seen, determine with laboratory 

analysis if the particles are 73-tooth or 41- 

tooth gearshaft material. 

(iv) If the particles are 73-tooth or 41-tooth 

gearshaft material, remove the affected 

gearshaft(s) within 75 FHs since the AGB/

TGB MCD inspection. 


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