Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 46729 

more effective method than Modification TU 

147 to reduce the risk of uncoupling between 

the low-pressure (LP) fuel pump impeller 

and the high-pressure (HP) fuel pump shaft 

of the HP/LP pump and hydro-mechanical 

metering unit (HMU). We are issuing this AD 

to prevent failure of the HMU. The unsafe 

condition, if not corrected, could result in 

failure of the engine, in-flight shutdown, and 

loss of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Check the transmissible torque between 

the LP fuel pump impeller and the HP fuel 

pump shaft as follows: 

(i) For pre-Modification TU 147 HMUs, 

check the torque before accumulating 500 

engine flight hours (FHs) since March 11, 

2010 or before the next flight, whichever 

occurs later. Use Paragraph 2 of Turbomeca 

Alert Mandatory Service Bulletin (MSB) 

A292 73 2830, Version B, dated July 10, 2009 

to do the check. 

(ii) For HMUs that incorporated 

Modification TU 147 on or before March 31, 

2010, and those HMUs not listed in Figures 

2 or 3 of Turbomeca Alert MSB A292 73 

2836, Version A, dated August 17, 2010, 

check the torque before the next flight. Use 

Paragraph 2 of Turbomeca Alert MSB A292 

73 2836, Version A, to do the check. 

(2) If the HMU does not pass the torque 

check, replace the HMU with a postModification TU 178 HMU before the next 

flight. 

(g) Mandatory Terminating Action 

Within 2,200 engine FHs or 72 months 

after the effective date of this AD, whichever 

occurs first, replace any pre-Modification TU 

178 HMU with a post-Modification TU 178 

configuration HMU. 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install a pre-Modification TU 178 HMU on 

engines incorporating a post-Modification TU 

178 HMU. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, may 

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. You may email your request to: 

ANE-AD-AMOC@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. 

(j) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2017–0102, dated June 13, 

2017, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2009–0889. 

(3) For service information identified in 

this AD, contact Safran Helicopter Engines, 

S.A., 40220 Tarnos, France; phone: (33) 05 59 

74 40 00; fax: (33) 05 59 74 45 15. You may 

view this referenced service information at 

the FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

Issued in Burlington, Massachusetts, on 

September 29, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–21344 Filed 10–5–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0902; Product 

Identifier 2016–NM–188–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2004–03– 

07, which applies to certain Airbus 

Model A320–111, –211, –212, and –231 

series airplanes. AD 2004–03–07 

requires repetitive inspections for 

fatigue cracking around the fasteners 

attaching the pressure panel to the 

flexible bracket at frame (FR) 36, 

adjacent to the longitudinal beams on 

the left and right sides of the airplane; 

and repair as necessary. Since we issued 

AD 2004–03–07, additional cracking has 

been found under the longitudinal 

beams in locations outside of the 

inspection areas required by AD 2004– 

03–07. This proposed AD would retain 

certain requirements of AD 2004–03–07, 

expand the applicability, and require an 

inspection of the fastener holes on the 

pressure panel between FR 35 and FR 

36 under the longitudinal beam and 

modification or repair as applicable. We 

are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 20, 

2017. 

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 NPRM, contact Airbus, 

Airworthiness Office—EIAS, 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 

Standards Branch, 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–2017– 

0902; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–0902; Product Identifier 2016– 

NM–188–AD at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 


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46730 Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 

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 January 29, 2004, we issued AD 

2004–03–07, Amendment 39–13451 (69 

FR 5907, February 9, 2004) (‘‘AD 2004– 

03–07’’), for certain Airbus Model 

A320–111, –211, –212, and –231 series 

airplanes. AD 2004–03–07 was 

prompted by fatigue tests which 

revealed cracking around the fasteners 

attaching the pressure panel to the 

flexible bracket at FR 36, adjacent to the 

longitudinal beams on the left and right 

sides of the airplane. Investigation 

revealed that the damage was caused by 

high loads in this area. AD 2004–03–07 

requires repetitive inspections for 

fatigue cracking around the fasteners 

attaching the pressure panel to the 

flexible bracket at FR 36, adjacent to the 

longitudinal beams on the left and right 

sides of the airplane; and repair as 

necessary. AD 2004–03–07 also 

provides an optional terminating action 

for the repetitive inspections. We issued 

AD 2004–03–07 to detect and correct 

fatigue cracking around the fasteners 

attaching the pressure panel to the 

flexible bracket at the FR 36 adjacent to 

the longitudinal beams, which could 

result in reduced structural integrity 

and possible rapid decompression of the 

airplane. 

Since we issued AD 2004–03–07, 

additional cracks have been found 

under the longitudinal beams at 

locations that are not included in the 

inspection area required by AD 2004– 

03–07. Fatigue and damage tolerance 

analyses were performed and the results 

indicated that all the holes in the 

pressure panel above the longitudinal 

beams have to be cold worked. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0206, dated October 13, 

2016; corrected October 14, 2016 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain Airbus Model 

A318 and Model A319 series airplanes, 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes, and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. The 

MCAI states: 

During fatigue tests, cracks were found 

around the fasteners connecting the pressure 

panel with the flexible bracket at fuselage 

frame (FR) 36, adjacent to the longitudinal 

beams on left-hand (LH) and right-hand (RH) 

sides. 

This condition, if not detected and 

corrected, could impair the structural 

integrity of the aeroplane. 

To address this unsafe condition, DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France issued [French] AD 2000–531–155(B) 

[which corresponds with FAA AD 2004–03– 

07] to require repetitive inspections of the 

longitudinal beams of the FR 36 pressure 

panel and, depending on findings, the 

accomplishment of a repair. 

Since that [French] AD was issued, 

additional cracks have been found under the 

beams, but in locations not covered by the 

required inspections. Fatigue and damage 

tolerance analyses were performed, the 

results of which indicated that all the holes 

in the pressure panel above all the 

longitudinal beams have to be cold worked. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France AD 2000–531–155(B), which is 

superseded, extends the applicability to all 

A320 family aeroplanes and requires [a 

special detailed inspection of the fastener 

holes on the pressure panel between FR35 

and FR36 under the longitudinal beam and] 

modification [or repair] of all the affected 

holes. 

This [EASA] AD is republished to correct 

the number of the superseded DGAC AD. 

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–2017– 

0902. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–53–1264, Revision 01, dated July 

4, 2016. The service information 

describes procedures for a special 

detailed inspection (rotating probe) for 

cracking of the fastener holes on the 

pressure panel between FR 35 and FR 

36 under the longitudinal beam and 

repair of any crack. 

Airbus has also issued Service 

Bulletin A320–53–1240, Revision 01, 

dated April 4, 2016, which describes 

procedures for modifying the pressure 

panel above the left and right 

longitudinal beams, including related 

investigative action (e.g., high frequency 

eddy current (rototest) inspection of all 

the removed fastener holes) and 

corrective actions (e.g., repair), by cold 

working the attachment holes under the 

longitudinal beam at FR 36 for airplanes 

on which no cracking was found. 

In addition, Airbus issued Service 

Bulletin A320–53–1263, Revision 01, 

dated February 29, 2016, which 

describes procedures for modifying the 

pressure panel above the left and right 

longitudinal beams, including related 

investigative actions (e.g., eddy current 

rotating probe inspection of the fastener 

holes) and corrective actions (e.g., 

repair), by adding a doubler and a filler, 

and cold expansion of the holes under 

the longitudinal beam at FR 36 for 

airplanes on which cracking was found. 

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. 

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 these same 

type designs. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

The MCAI specifies that operators can 

calculate revised thresholds for Model 

A319 and A320 series airplanes with 

sharklets installed (Airbus Service 

Bulletin A320–57–1193). This proposed 

AD does not include those calculations 

because the calculations could result in 

different inspection thresholds for each 

individual airplane. However, under the 

provisions of paragraph (o)(1) of this 

AD, we will consider requests for 

approval of alternative compliance 

times. 

Costs of Compliance 

We estimate that this proposed AD 

affects 737 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 46731 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspection [Retained 

from AD 2004–03–07].

Up to 2 work-hours × $85 per hour = $170 per 

inspection cycle.

$0 Up to $170 per inspection cycle.Up to $125,290 per inspection cycle. 

Inspection [new proposed requirement].13 work-hours × $85 per hour = $1,105 ............ 0 $1,105 .......................... $814,385. 

We estimate the following costs to do 

any necessary modifications that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these modifications: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Modification .......................... Up to 213 work-hours × $85 per hour = $18,105 ......... Up to $8,510 ...................... Up to $26,615. 

Reporting ............................. 1 work-hour × $85 per hour = $85 ................................ $0 ....................................... $85. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition repairs 

specified in the service information. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this NPRM is 2120–0056. 

The paperwork cost associated with this 

NPRM has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this NPRM is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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. 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 

FAA Order 8000.51C. In accordance 

with that order, issuance of ADs is 

normally a function of the Compliance 

and Airworthiness Division, but during 

this transition period, the Executive 

Director has delegated the authority to 

issue ADs applicable to transport 

category airplanes to the Director of the 

System Oversight Division. 

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 

■ 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) 

2004–03–07, Amendment 39–13451 (69 

FR 5907, February 9, 2004), and adding 

the following new AD: 

Airbus: Docket No. FAA–2017–0902; Product 

Identifier 2016–NM–188–AD. 

(a) Comments Due Date 

We must receive comments by November 

20, 2017. 

(b) Affected ADs 

This AD replaces AD 2004–03–07, 

Amendment 39–13451 (69 FR 5907, February 

9, 2004) (‘‘AD 2004–03–07’’). 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, 

except for airplanes on which Airbus 

Modification 151574 was embodied in 

production. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 


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46732 Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by fatigue tests 

which revealed cracking around the fasteners 

attaching the pressure panel to the flexible 

bracket at frame (FR) 36, adjacent to the 

longitudinal beams on the left and right sides 

of the airplane. We are issuing this AD to 

detect and correct fatigue cracking around 

the fasteners attaching the pressure panel to 

the flexible bracket at the FR 36 adjacent to 

the longitudinal beams, which could result in 

reduced structural integrity of the airplane 

and possible rapid decompression of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection and Follow-On 

Actions, With No Changes 

This paragraph restates the requirements of 

paragraphs (a) and (b) of AD 2004–03–07, 

with no changes. 

(1) For Model A320–211, –212, and –231 

series airplanes having serial numbers 0002 

through 0107 inclusive, except those 

airplanes on which Airbus Modification 

21202/K1432 has been incorporated in 

production, or on which Airbus Service 

Bulletin A320–53–1029, Revision 01, dated 

April 29, 2002, has been incorporated: Prior 

to the accumulation of 30,000 total flight 

cycles, do a rotating probe inspection on 

airplanes with a center fuel tank, or a 

detailed inspection on airplanes without a 

center fuel tank, to detect cracking around 

the fasteners that attach the pressure panel to 

the flexible bracket at FR 36, adjacent to the 

longitudinal beams on the left and right sides 

of the airplane, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1030, Revision 01, 

dated May 21, 2002. 

(2) If no crack is detected by the inspection 

required by paragraph (g)(1) of this AD, 

repeat the applicable inspection thereafter at 

intervals not to exceed 6,000 flight cycles for 

airplanes without a center fuel tank, and at 

intervals not to exceed 18,000 flight cycles 

for airplanes with a center fuel tank. 

(h) Retained Corrective Actions, With 

Specific Delegation Approval Language 

This paragraph restates the requirements of 

paragraphs (c) and (d) of AD 2004–03–07, 

with specific delegation approval language. 

(1) If any crack is detected during any 

inspection required by paragraph (g)(1) of 

this AD, before further flight, repair the 

affected structure by accomplishing all 

applicable actions in accordance with 

paragraphs 3.B. through 3.E. of the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1030, Revision 01, 

dated May 21, 2002. Repeat the applicable 

inspection thereafter at intervals not to 

exceed 6,000 flight cycles for airplanes 

without a center fuel tank, and at intervals 

not to exceed 18,000 flight cycles for 

airplanes with a center fuel tank. For any 

area where cracking is repaired, the repair 

constitutes terminating action for the 

repetitive inspection of that area. 

Note 1 to paragraph (h)(1) of this AD: 

Airbus Service Bulletin A320–53–1030 

references Airbus Service Bulletin A320–53– 

1029, Revision 01, dated April 29, 2002, as 

an additional source of service information 

for certain repairs. 

(2) If Airbus Service Bulletin A320–53– 

1030, Revision 01, dated May 21, 2002, 

specifies to contact the manufacturer for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (o)(2) of this AD. 

(i) Retained Optional Terminating Action for 

Paragraphs (g) and (h) of This AD, With 

Revised Compliance Language 

This paragraph restates the requirements of 

paragraph (e) of AD 2004–03–07, with 

revised compliance language. For Model 

A320–211, –212, and –231 series airplanes 

having serial numbers 0002 through 0107 

inclusive, except those airplanes on which 

Airbus Modification 21202/K1432 has been 

incorporated in production, or Airbus 

Service Bulletin A320–53–1029, Revision 01, 

dated April 29, 2002: Modification, before 

the effective date of this AD, of the structure 

around the fasteners that attach the pressure 

panel to the flexible bracket at FR 36, 

adjacent to the longitudinal beams on the left 

and right sides of the airplane, by 

accomplishing all applicable actions in 

accordance with paragraphs 3.A. through 3.E. 

of the Accomplishment Instructions of 

Airbus Service Bulletin A320–53–1029, 

Revision 01, dated April 29, 2002, constitutes 

terminating action for the actions required by 

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

(j) New Requirement of This AD: Inspection 

For all airplanes, except for airplanes 

identified in paragraph (l) of this AD: At the 

applicable time specified in table 1 to 

paragraph (j) of this AD, do a special detailed 

inspection for cracking of the fastener holes 

on the pressure panel between FR 35 and FR 

36 under the longitudinal beam, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1264, Revision 01, dated July 4, 2016. 

BILLING CODE 4910–13–P 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS

EP06OC17.000</GPH>asabaliauskas on DSKBBXCHB2PROD with PROPOSALS

Table 1 to Paragraph G) of this AD - Pressure Panel Inspection /Modification Thresho

Time accumulated by the airplane on the Complian

effective date of this AD 

Affected airplanes (flight cycles and flight hours since the airplane's (flight cycles or flight h

first flight) tlrs

A: Before accumulating 12,

flight hours since the airplan

All airplanes, except Model Less than 12,000 flight cycles and 24,000 flight hours A318 Elite airplanes; Model B: Within 5,000 flight cycle

A319CJ airplanes (Corporate after the effective date ofthi

Jet- airplanes equipped with whichever occurs later, A or 

Modifications 2823 8, 28162, 

Within 5,000 flight cycles o

and 28342); Airbus Model 

A319 series airplanes on 12,000 flight cycles or 24,000 flight hours or more, but the effective date of this AD

which the actions specified in less than 30,000 flight cycles and 60,000 flight hours 33,000 flight cycles or 66,00

Airbus Service Bulletin airplane's first flight 

A320-57-1193 have been Within 3,000 flight cycles or 

embodied (sharklets installed 30,000 flight cycles or 60,000 flight hours or more, but the effective date 

as retrofit); Airbus Model less than 40,000 flight cycles and 80,000 flight hours ofthis AD, without exceedin

A320 series airplanes on 83,600 flight hours since the 

which the actions specified in 

Airbus Service Bulletin Within 1,800 flight cycles o

A320-57-1193 have been 40,000 flight cycles or 80,000 flight hours or more, but the effective date of this AD

embodied (sharklets installed less than 44,000 flight cycles and 88,000 flight hours 44,600 flight cycles or 89,20

as retrofit) airplane's first flight 

44,000 flight cycles or 88,000 flight hours or more Within 600 flight cycles or 

effective date of this AD 

EP06OC17.001</GPH>asabaliauskas on DSKBBXCHB2PROD with PROPOSALS

Time accumulated by the airplane on the Complian

effective date of this AD 

Affected airplanes (flight cycles and flight hours since the airplane's (flight cycles or flight h

first flight) firs

A: Before accumulating 11,

33,900 flight hours since air

Less than 11,300 flight cycles and 33,900 flight hours B: Within 2,500 flight cycle

Model A318 Elite airplanes after the effective date of thi

whichever occurs later, A or 

11,300 flight cycles or 33,900 flight hours or more Within 2,500 flight cycles o

the effective date of this AD 

A: Before accumulating 6,30

flight hours since airplane fi

Less than 6,300 flight cycles and 27,000 flight hours B: Within 2,300 flight cycle

Model A319 CJ airplanes on after the effective date ofthi

which the actions specified in whichever occurs later, A or 

Airbus Service Bulletin 

A320-57-1193 have not been Within 2,300 flight cycles o

embodied (sharklets not 6,300 flight cycles or 27,000 flight hours or more, but the effective date of this AD

installed) less than 14,300 flight cycles and 68,300 flight hours 15,700 flight cycles or 75,10

airplane's first flight 

14,300 flight cycles or 68,300 flight hours or more Within 1,400 flight cycles o

the effective date of this AD 

EP06OC17.002</GPH>asabaliauskas on DSKBBXCHB2PROD with PROPOSALS

Time accumulated by the airplane on the Complian

effective date of this AD 

Affected airplanes (flight cycles and flight hours since the airplane's (flight cycles or flight h

first flight) firs

A: Before accumulating 9,80

flight hours since the airplan

Less than 9,000 flight cycles and 18,000 flight hours B: Within 3,300 flight cycle

after the effective date of thi

whichever occurs later, A or

Within 3,300 flight cycles o

9,000 flight cycles or 18,000 flight hours or more, but the effective date of this AD

Model A319 and A320 series less than 24,000 flight cycles and 48,000 flight hours 25,300 flight cycles or 50,60

airplanes on which the actions airplane's first flight* Within 1,300 flight cycles o

specified in Airbus Service 24,000 flight cycles or 48,000 flight hours or more, but the effective date of this AD

Bulletin A320-57-1193 have 

been embodied (sharklets less than 30,000 flight cycles and 60,000 flight hours 30,700 flight cycles or 61,40

airplane's first flight* installed) Within 700 flight cycles or 

30,000 flight cycles or 60,000 flight hours or more, but effective date of this AD, wi

less than 32,000 flight cycles and 64,000 flight hours flight cycles or 64,600 flight 

first flight* 

Within 300 flight cycles or 6

32,000 flight cycles or 64,000 flight hours or more, but effective date of this AD, wi

less than 33,000 flight cycles and 66,000 flight hours flight cycles or 66,000 flight 

first flight; or within 30 day

this AD; whichever occurs l
BILLING CODE 4910–13–C 


EP06OC17.003</GPH>asabaliauskas on DSKBBXCHB2PROD with PROPOSALS

Time accumulated by the airplane on the Comp

effective date of this AD 

Affected airplanes (flight cycles or fligh

(flight cycles and flight hours since the 

airplane's first flight) 

A: Before accumulat

19,600 flight hours s

Less than 4,200 flight cycles and 18,000 flight flight; or 

hours B: Within 1,600 fligh

hours after the effect

whichever occurs lat

Model A319 airplanes used as CJ post Airbus 

4,200 flight cycles or 18,000 flight hours or Within 1,600 flight c

Service Bulletin A320-57-1193 after the effective da

more, but less than 14,300 flight cycles and exceeding 15,300 fli

61,400 flight hours hours since the airpl

14,300 flight cycles or 61,400 flight hours or Within 1,000 flight c

more but less than 18,000 flight cycles or after the effective da

77,400 flight hours 

For A319 and A320 airplanes with a sharklet installed as a retrofit (post-Airbus Service Bulletin A320-57-1193 (post-mo

determining an alternative compliance time for the initial inspection can be found in in "Compliance Time" ofPart 2, Da

Airworthiness Limitation Items, of the Model A318/ A319/ A320/ A321 Airworthiness Limitations Section; however, to u

compliance time, operators must request an alternative method of compliance using a method approved in accordance w

specified in paragraph ( o )(I) of this AD. 

* Without exceeding the time at which an inspection is required through the threshold or compliance time of a Model A3

Service Bulletin A320-57-1193 (pre-mod 160080). 

* * Without exceeding the time at which an inspection is required through the threshold or compliance time of a Model A

pre-Airbus Service Bulletin A320-57-ll93 (pre-mod 160080). 
Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 46737 

(k) On-Condition Actions 

(1) If, during any inspection required by 

paragraph (j) of this AD, no cracking is found, 

or cracking is found that is within the limits 

specified in Airbus Service Bulletin A320– 

53–1264, Revision 01, dated July 4, 2016: 

Before further flight, modify the pressure 

panel above the left and right longitudinal 

beams, including doing all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1240, Revision 01, dated April 4, 2016; or 

Service Bulletin A320–53–1263, Revision 01, 

dated February 29, 2016; as applicable. Do all 

related investigative and corrective actions 

before further flight. Where Airbus Service 

Bulletin A320–53–1240, Revision 01, dated 

April 4, 2016; and Service Bulletin A320–53– 

1263, Revision 01, dated February 29, 2016; 

specify to contact Airbus for appropriate 

action: Before further flight, accomplish the 

repair in accordance with the procedures 

specified in paragraph (o)(2) of this AD. 

(2) If, during any inspection required by 

paragraph (j) of this AD, any cracking is 

found that exceeds the limits specified in 

Airbus Service Bulletin A320–53–1264, 

Revision 01, dated July 4, 2016: Do the 

actions specified in, and at the compliance 

times specified in, paragraphs (k)(2)(i) and 

(k)(2)(ii) of this AD. 

(i) Before further flight, repair any cracking 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1264, Revision 01, dated July 4, 2016. 

Where Airbus Service Bulletin A320–53– 

1264, Revision 01, dated July 4, 2016, 

specifies to contact Airbus for appropriate 

action, and specifies that action as ‘‘RC’’ 

(Required for Compliance): Before further 

flight, request approval of repair instructions 

using a method approved in accordance with 

the procedures specified in paragraph (o)(2) 

of this AD, and accomplish the repair 

accordingly within the compliance time 

specified in those instructions. If no 

compliance time is defined in the repair 

instructions, accomplish the repair before 

further flight. 

(ii) At the times specified in paragraph 

(k)(2)(ii)(A) or (k)(2)(ii)(B) of this AD, as 

applicable: Report any findings of cracking 

that exceeds the limits specified in Airbus 

Service Bulletin A320–53–1264, Revision 01, 

dated July 4, 2016, to Airbus Customer 

Services through TechRequest on Airbus 

World (https://w3.airbus.com/) by selecting 

Engineering Domain and ATA 57–10. 

(A) If the inspection was done on or after 

the effective date of this AD: Report within 

90 days after that inspection. 

(B) If the inspection was done before the 

effective date of this AD: Report within 90 

days after the effective date of this AD. 

(l) Actions for Certain Airplanes 

For Model A319 and Model A320 series 

airplanes on which the actions specified in 

Airbus Service Bulletin A320–57–1193 have 

been embodied and the airplane has 

accumulated 33,000 flight cycles or 66,000 

flight hours or more since the airplane’s first 

flight on the effective date of this AD: Within 

30 days after the effective date of this AD, 

contact the Manager, International Section, 

Transport Standards Branch FAA; or the 

EASA; or Airbus’s EASA DOA for approved 

repair instructions and within the 

compliance time specified in those 

instructions, accomplish the repair 

accordingly. If no compliance time is defined 

in the repair instructions, accomplish the 

repair before the next flight. 

(m) Terminating Action for Repetitive 

Inspections Required by Paragraph (g)(2) of 

This AD 

(1) Modification of an airplane as specified 

in paragraph (m)(1)(i), (m)(1)(ii), or (m)(1)(iii) 

of this AD constitutes terminating action for 

the repetitive inspection required by 

paragraph (g)(2) of this AD for that airplane 

only. 

(i) Modification of an airplane as required 

by paragraph (k)(1) of this AD. 

(ii) Modification of an airplane prior to the 

effective date of this AD, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1240, dated March 

19, 2015; or Airbus Service Bulletin A320– 

53–1263, dated March 19, 2015; as 

applicable. 

(iii) Modification of an airplane using 

instructions obtained in accordance with the 

procedures specified in paragraph (o)(2) of 

this AD. 

(2) Repair of an airplane as required by 

paragraph (k)(2) of this AD constitutes 

terminating action for the repetitive 

inspections required by paragraph (g)(2) of 

this AD for that airplane, unless specified 

otherwise in the repair instructions approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

EASA; or Airbus’s EASA DOA. 

(n) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (g) and (h)(1) 

of this AD, if those actions were performed 

before March 15, 2004 (the effective date of 

AD 2004–03–07) using Airbus Service 

Bulletin A320–53–1030, dated January 5, 

2000; or Airbus Service Bulletin A320–53– 

1029, dated January 5, 2000. 

(2) This paragraph provides credit for 

actions required by paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–53–1264, dated March 19, 

2015. 

(3) This paragraph provides credit for 

actions required by paragraph (k)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–53–1240, dated March 

19, 2015; or Airbus Service Bulletin A320– 

53–1263, dated March 19, 2015; for that 

airplane only. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 the attention of the person identified 

paragraph (p)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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 Section, Transport 

Standards Branch, 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. 

(3) Required for Compliance (RC): Except 

as required by paragraph (k)(2)(i) of this AD: 

If any 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 or 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 an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(4) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0206, dated October 13, 2016; corrected 

October 14, 2016; 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–2017–0902. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
46738 Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules 

Renton, WA 98057–3356; telephone 425– 

227–1405; fax 425–227–1149. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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 Standards Branch, 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 

September 21, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Branch, 

Aircraft Certification Service. 

[FR Doc. 2017–21221 Filed 10–5–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No.: FAA–2017–0879] 

RIN 2120–AA65 

Criteria and Process for the 

Cancellation of Standard Instrument 

Approach Procedures as Part of the 

National Procedures Assessment 

(NPA) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Proposed policy and request for 

comment. 

SUMMARY: As new technology facilitates 

the introduction of area navigation 

(RNAV) instrument approach 

procedures over the past decade, the 

number of procedures available in the 

National Airspace System has nearly 

doubled. The complexity and cost to the 

Federal Aviation Administration (FAA) 

of maintaining the instrument flight 

procedures inventory while expanding 

the new RNAV capability is not 

sustainable. The FAA is considering the 

cancellation of certain circling 

procedures (to include circling-only 

instrument approach procedures (IAPs) 

and circling minima charted on straightin IAPs). The FAA proposes specific 

criteria to guide the identification and 

selection of appropriate circling 

procedures that can be considered for 

cancellation. The circling procedures 

associated with this cancellation 

initiative would be selected from the 

criteria outlined below. This document 

is not a part of the FAA’s VOR 

minimum operating network (MON) 

initiative. 

DATES: Comments must be received on 

or before November 6, 2017. 

ADDRESSES: Send comments identified 

by docket number FAA–2017–0879 

using any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: In accordance with 5 U.S.C. 

553(c), DOT solicits comments from the 

public to better inform its rulemaking 

process. DOT posts these comments, 

without edit, including any personal 

information the commenter provides, to 

www.regulations.gov, as described in 

the system of records notice (DOT/ALL– 

14 FDMS), which can be reviewed at 

www.dot.gov/privacy. 

Docket: Background documents or 

comments received may be read at 

http://www.regulations.gov at any time. 

Follow the online instructions for 

accessing the docket or go to the Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Lonnie Everhart, 

Aeronautical Information Services AJV– 

5, Federal Aviation Administration, Air 

Traffic Organization, 6500 S. MacArthur 

Blvd, Oklahoma City, OK 73169; 

Telephone (405) 954–4576; Email AMCATO-IFP-Cancellations@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

Under 49 U.S.C. 40103(a), the 

Administrator has broad authority to 

regulate the safe and efficient use of the 

navigable airspace. The Administrator is 

also authorized to issue air traffic rules 

and regulations to govern the flight, 

navigation, protection, and 

identification of aircraft for the 

protections of persons and property on 

the ground and for the efficient use of 

the navigable airspace. 49 U.S.C. 

40103(b). Under Section 44701(a)(5), the 

Administrator promotes safe flight of 

civil aircraft in air commerce by 

prescribing regulations and minimum 

standards for other practices, methods, 

and procedures necessary for safety in 

air commerce and national security. 

This action is within the scope of that 

authority. 

IAPs are promulgated by rulemaking 

procedures and are incorporated by 

reference pursuant to 5 U.S.C. 552(a) 

and 1 CFR part 51 into Title 14 of the 

Code of Federal Regulations; Part 97 (14 

CFR part 97), Subpart C—TERPS 

Procedures. 

Background 

The National Airspace System (NAS) 

is currently in transition to a ‘‘NextGen 

NAS’’. During this transition, the FAA 

is managing the technology and 

procedures to support both the Legacy 

NAS as well as the NextGen NAS. 

Managing two versions of the NAS 

requires excess manpower, 

infrastructure, and information 

management which is costly and 

unsupportable in the longterm. To 

mitigate these costs, the FAA has a 

number of efforts underway to 

effectively transition from the legacy to 

the NextGen NAS. One area of focus for 

this transition is instrument flight 

procedures (IFPs). The FAA seeks to 

ensure an effective transition from 

ground-based IFPs to greater availability 

and use of satellite-based IFPs while 

maintaining NAS safety. 

In early 2015, the FAA requested the 

RTCA’s Tactical Operations Committee 

(TOC) with providing feedback and 

recommendations on criteria and 

processes for cancelling instrument 

flight procedures. Among the many 

recommendations provided by the TOC 

were criteria on how to identify circling 

procedures that would qualify as 

candidates for cancellation. As of the 

beginning of 2017, there are 

approximately 12,000 IAPs in 

publication, and there were nearly 

10,600 circling lines of minima. Circling 

procedures account for approximately 

one-third of all lines of minima in the 

NAS. 

In its continued effort to right-size the 

NAS through optimization and 

elimination of redundant and 

unnecessary IAPs, the FAA proposes the 

following criteria to guide the 

identification and selection of 

appropriate circling procedures to be 

considered for cancellation. 

It should be noted that National 

Procedures Assessment (NPA) 

Instrument Flight Procedure (IFP) 

cancellation activities and associated 

criteria do not supersede similar 

activities being performed under the 


asabaliauskas on DSKBBXCHB2PROD with PROPOSALS