Federal Register / Vol. 82, No. 48 / Tuesday, March 14, 2017 / Proposed Rules 13567 

0–00 with P/N MC7015–1–00. P/N MC7014– 

1–00 and P/N MC7015–1–00 must be from 

the same manufacturer. 

(iii) Modify and re-identify the helicopter 

wiring harness. Refer to Figure 3 of 

Eurocopter Alert Service Bulletin No. EC225– 

05A033, Revision 0, dated July 14, 2013 (ASB 

EC225–05A033). 

(iv) Replace MGB lubrication card P/N 

704A46580127 with P/N 704A46580146, and 

MGB lubrication card P/N 704A46580106 

with P/N 704A46580146 or –147. 

(v) Accomplish a functional test of the 

EMLUB system and the electrical system. 

(vi) Revise the Emergency Procedures 

section of the Rotorcraft Flight Manual (RFM) 

by removing any pages from Section 3 of the 

RFM that pertain to the emergency 

procedures in the event of EMLUB activation 

and by inserting the pages from paragraph 

4.C. Appendix 3, of ASB EC225–05A033 into 

Section 3 of the RFM. 

(2) Do not install on any helicopter EMLUB 

glycol pump P/N 332A32–5051–00, air 

pressure-switch P/N MA193–00 or P/N 

MC7014–0–00, glycol pressure-switch P/N 

MA194–01 or P/N MC7015–0–00, or 

electronic board P/N 704A46580106 or P/N 

704A46580127. 

(f) Special Flight Permit 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to Rao Edupuganti, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

10101 Hillwood Pkwy., Fort Worth, Texas 

76177; telephone (817) 222–5110; email 

rao.edupuganti@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

(1) Emergency Alert Service Bulletin (ASB) 

No.05A032, Revision 2, dated July 14, 2013, 

and Emergency ASB with two numbers (No. 

04A010 and No. 04A009), Revision 1, dated 

July 14, 2013, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Airbus Helicopters, 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.com/techpub. You 

may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

Texas 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

2013–0156, dated July 18, 2013. You may 

view the EASA AD on the Internet at http:// 

www.regulations.gov in Docket No. FAA– 

2016–9143. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6320, Main Rotor Gearbox. 

Issued in Fort Worth, Texas, on March 1, 

2017. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2017–04736 Filed 3–13–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4007; Directorate 

Identifier 2015–SW–064–AD] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Model 234 and Model CH–47D 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for various 

Model 234 and Model CH–47D 

helicopters. This proposed AD would 

require inspections of the pitch housing 

and revising the pitch housing 

retirement life. This proposed AD is 

prompted by reports of cracking in the 

pitch housing lugs. The proposed 

actions are intended to detect and 

prevent an unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by May 15, 2017. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

4007; 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 proposed AD, the 

economic evaluation, the Special 

Airworthiness Information Bulletin 

(SAIB), 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 service information identified in 

this proposed AD, contact Boeing 

Helicopters, The Boeing Company, 1 S. 

Stewart Avenue, Ridley Park, PA 19078, 

telephone 610–591–2121, and Columbia 

Helicopters, Inc. (Columbia), 14452 

Arndt Road NE., Aurora OR 97002, 

telephone (503) 678–1222, fax (503) 

678–5841, or at http://www.colheli.com. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. 

FOR FURTHER INFORMATION CONTACT: 

Kathleen Arrigotti, Aerospace Engineer, 

Seattle Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057; telephone (425) 

917–6426; email Kathleen.Arrigotti@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 


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13568 Federal Register / Vol. 82, No. 48 / Tuesday, March 14, 2017 / Proposed Rules 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

We propose to adopt an AD for 

helicopters with a pitch housing part 

number (P/N) 145R2075–11, 145R2075– 

12, 145R2075–13, 145R2075–14, 

145R2075–15, 145R2075–16, 234R2075– 

1, or 234R2075–2 installed. These pitch 

housings are installed on Model 234 and 

Model CH–47D helicopters. The type 

certificate (TC) holder for Model 234 

helicopters is Columbia (type certificate 

previously held by Boeing Defense & 

Space Group), and the type certificate 

holders for Model CH–47D helicopters 

currently include Columbia, Billings 

Flying Service, Inc., and Tandem Rotor, 

LLC. We are not limiting this proposed 

AD to the type certificate holders listed 

above because we expect additional 

type certificate holders of helicopters 

that are subject to this same unsafe 

condition. 

This proposed AD is prompted by 

reports of cracking in the pitch housing 

lugs. In November 2007, Boeing 

reported the failure of an aft rotor pitch 

housing lower lug on a Model CH–47 

helicopter operated by the Japanese 

Ground Self Defense Force. On March 

26, 2009, a Model 234 helicopter also 

experienced a failure because of a crack 

on an aft rotor pitch housing lower lug. 

In both cases, the cracking was located 

on the lead side of the lower vertical pin 

lug and had initiated in the bore. The 

crack grew outward by fatigue, initiated 

by fretting damage. 

Those incidents prompted the FAA to 

issue SAIB SW–11–03, dated October 

22, 2010. The SAIB recommends that all 

owners and operators of Columbia 

Model 234 helicopters perform 

repetitive ultrasonic inspections of the 

lugs. At that time, there were no civil 

Model CH–47D helicopters in service. 

On March 20, 2015, we received a 

report of lateral vibration on a Model 

234 helicopter that prompted an 

immediate landing. A subsequent 

investigation found that a crack in an aft 

pitch housing upper lug resulted in the 

lateral vibrations. The pitch housing 

had accumulated 11,733 hours time-inservice (TIS). The crack was determined 

to be caused by fatigue and attributed to 

underestimated load conditions in the 

original life limit calculations. This 

cracking differed from the cracking 

described in the SAIB because the 

cracking initiated at the outer surface of 

the pitch housing lug and grew inward 

toward the bore. 

To correct this unsafe condition, we 

propose to require repetitive eddy 

current and ultrasonic inspections of the 

pitch housing. Based on the proximity 

of the most recent inward-growing crack 

to the outward cracks described in the 

SAIB, we propose to require ultrasonic 

inspections of the pitch housing, as 

recommended in the SAIB. Boeing, the 

original manufacturer of both model 

helicopters, developed service 

information for the SAIB ultrasonic 

inspections, which we would require in 

this proposed AD. Due to the rapid 

growth rate, an effective eddy current 

inspection must detect an inwardgrowing crack of no more than 0.10 

inch. This proposed AD would require, 

for Columbia helicopters, the eddy 

current inspection method specified in 

Columbia’s service information. Because 

the other TC holders have not 

developed service instructions, we 

propose to require the eddy current 

inspection procedures for all other 

helicopters be submitted to the Seattle 

or Denver Aircraft Certification Offices 

for approval. 

We are also proposing to require 

removing the pitch housing from service 

when it accumulates a total of 8,200 

hours TIS. Forward pitch housings on 

Model CH–47D helicopters have no life 

limit and the aft pitch housing already 

has a life limit of 8,200 hours TIS. For 

Model 234 helicopters, the forward 

pitch housing has a life limit of 12,547 

hours TIS and the aft pitch housing has 

a life limit of 19,077 hours TIS. This 

proposed AD would establish or reduce 

these life limits to 8,200 hours TIS for 

both forward and aft pitch housings, 

regardless of the model helicopter. 

The actions specified by this 

proposed AD are intended to detect and 

prevent a crack in a pitch housing lug. 

This condition could result in loss of a 

rotor blade and consequent loss of 

helicopter control. 

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. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Service Bulletin 

145R2075–62–0001, Revision 1, dated 

September 27, 2011, which specifies 

updated life limits for the forward and 

aft pitch housings and revised overhaul 

and ultrasonic inspection procedures for 

various military Model CH–47 and 234 

helicopters. 

We also reviewed Columbia 

Helicopters, Inc., Alert Service Bulletin 

No. 234–62–A0012, Revision 2, dated 

March 1, 2016, for Model 234 

helicopters; and Alert Service Bulletin 

No. 47D–62–A0002, Revision 0, dated 

March 1, 2016, for Model CH–47D 

helicopters. This service information 

specifies procedures for performing 

repetitive eddy current inspections, 

visual inspections, and ultrasonic 

inspections and for reducing the life 

limit of the pitch housing assemblies. 

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. 

Proposed AD Requirements 

This proposed AD would require: 

Before further flight, removing from 

service any pitch housing P/N 

145R2075–11, 145R2075–12, 145R2075– 

13, 145R2075–14, 145R2075–15, 

145R2075–16, 234R2075–1, and 

234R2075–2 that has accumulated 8,200 

hours total time-in-service (TIS). 

Before the pitch housing accumulates 

200 hours TIS after the effective date of 

this proposed AD and thereafter at 

intervals not to exceed 200 hours TIS, 

ultrasonic inspecting the pitch housing 

for a crack and replacing any cracked 

pitch housing. Within 400 hours TIS or 

before the pitch housing accumulates 

4,000 hours total TIS, whichever occurs 

later, and thereafter at intervals not to 

exceed 500 hours TIS, eddy current 

inspecting the pitch housing for a crack 

and replacing any cracked pitch 

housing. 

For Columbia helicopters, this eddy 

current inspection would be performed 

in accordance with the Columbia 

service information. For all other 

helicopters, this proposed AD would 

require that the method for the eddy 

current inspection be approved by the 

Manager, Seattle Aircraft Certification 

Office (ACO) or Manager, Denver ACO. 

Differences Between This Proposed AD 

and the Service Information 

The service information provides 

different life limits for the forward and 

aft pitch housings, while this proposed 

AD would require a life limit of 8,200 

hours TIS for all pitch housings. The 

service information requires either an 

ultrasonic inspection or a dye penetrant 

inspection as part of the overhaul 

procedures. The service information 

specifies different compliance times for 

the inspections than what would be 

required by this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 15 helicopters of U.S. 

Registry and that labor costs would 

average $85 per work-hour. Based on 


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these estimates, we expect the following 

costs: 

• An eddy current inspection would 

require 4 work-hours for a total cost of 

$340 per helicopter and $5,100 for the 

U.S. fleet, per inspection cycle. 

• An ultrasonic inspection would 

require 4 work-hours for a total cost of 

$340 per helicopter and $5,100 for the 

U.S. fleet, per inspection cycle. 

• Replacing a pitch housing would 

require 8 work-hours and parts would 

cost $13,000, for a total cost of $13,680 

per helicopter. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. For the reasons 

discussed, I certify that this proposed 

AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 adding 

the following new airworthiness 

directive (AD): 

Various Model 234 and Model CH–47D 

Helicopters: Docket No. FAA–2015– 

4007; Directorate Identifier 2015–SW– 

64–AD. 

(a) Applicability 

This AD applies to Model 234 and Model 

CH–47D helicopters, regardless of type 

certificate holder, with a pitch housing 

assembly (pitch housing) part number (P/N) 

145R2075–11, 145R2075–12, 145R2075–13, 

145R2075–14, 145R2075–15, 145R2075–16, 

234R2075–1, or 234R2075–2 installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a pitch housing lug. This condition 

could result in loss of a rotor blade and 

consequent loss of helicopter control. 

(c) Comments Due Date 

We must receive comments by May 15, 

2017. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Before further flight, remove from 

service any pitch housing P/N 145R2075–11, 

145R2075–12, 145R2075–13, 145R2075–14, 

145R2075–15, 145R2075–16, 234R2075–1, 

and 234R2075–2 that has accumulated 8,200 

hours total time-in-service (TIS). 

(2) Before the pitch housing accumulates 

200 hours TIS after the effective date of this 

AD and thereafter at intervals not to exceed 

200 hours TIS, ultrasonic inspect the pitch 

housing for a crack in accordance with 

Attachment 1, paragraphs F and H through K, 

of Boeing Service Bulletin 145R2075–62– 

0001, Revision 1, dated September 27, 2011. 

If there is a crack, replace the pitch housing 

before further flight. 

(3) Within 400 hours TIS or before the 

pitch housing has accumulated 4,000 hours 

total TIS, whichever occurs later, and 

thereafter at intervals not to exceed 500 hours 

TIS: 

(i) For Columbia Helicopters, Inc., Model 

234 and CH–47D helicopters, eddy current 

inspect the pitch housing for a crack by 

following paragraphs 3.C.(1) and 3.C.(2) of 

Columbia Helicopters, Inc., Alert Service 

Bulletin No. 234–62–A0012, Revision 2, 

dated March 1, 2016, or Alert Service 

Bulletin No. 47D–62–A0002, Revision 0, 

dated March 1, 2016, as applicable to your 

model helicopter. If there is a crack, replace 

the pitch housing before further flight. 

(ii) For all other helicopters, eddy current 

inspect the pitch housing for a crack. If there 

is a crack, replace the pitch housing before 

further flight. The eddy current inspection 

must be accomplished using a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO) or Manager, 

Denver ACO. For a repair method to be 

approved as required by this AD, the 

Manager’s approval letter must specifically 

refer to this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) For operators of helicopters with type 

certificates issued by the Denver Aircraft 

Certification Office, the manager of the 

Denver Aircraft Certification Office, FAA, 

may approve AMOCs for this AD. Send your 

proposal to: Greg Johnson, Senior Aerospace 

Engineer, Denver Aircraft Certification 

Office, 26805 East 68th Avenue, Denver, CO 

80249; phone: 303–342–1083; fax: 303–342– 

1088; email: Gregory.Johnson@faa.gov. 

(2) All other AMOC requests should be 

sent to the Manager, Seattle Aircraft 

Certification Office, FAA. Send your 

proposal to: Kathleen Arrigotti, Aerospace 

Engineer, Seattle Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue SW., Renton, Washington 

98057; telephone (425) 917–6426; email 9- 

ANM-Seattle-ACO–AMOC-Requests@faa.gov. 

(3) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

Special Airworthiness Information Bulletin 

SW–11–03, dated October 22, 2010 (SAIB), 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. You may view the SAIB 

on the internet at http://www.regulations.gov 

in the AD Docket. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220, Main Rotor Head. 

Issued in Fort Worth, Texas, on March 1, 

2017. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2017–04735 Filed 3–13–17; 8:45 am] 

BILLING CODE 4910–13–P 


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