Federal Register / Vol. 83, No. 110 / Thursday, June 7, 2018 / Proposed Rules 26383 

(c) Applicability 

This AD applies to Honda Aircraft 

Company LLC Model HA–420 airplanes, all 

serial numbers, that: 

(1) Have power brake valve, part number 

(P/N) HJ1–13243–101–005 or HJ1–13243– 

101–007, installed; and 

(2) are certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 32, Landing Gear. 

(e) Unsafe Condition 

This AD was prompted by reports of 

unannunciated asymmetric braking during 

ground operations and landing deceleration. 

We are issuing this AD to detect failure of the 

power brake valve (PBV). The unsafe 

condition, if not addressed, could result in 

degraded braking performance and reduced 

directional control during ground operations 

and landing deceleration. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Insert Temporary Revision Into the 

Airplane Flight Manual (AFM) 

Before further flight after May 29, 2018 (the 

effective date retained from AD 2018–11–05) 

insert Honda Aircraft Company Temporary 

Revision TR 01.1, dated February 16, 2018, 

into the Honda Aircraft Company (Honda) 

HA–420 Airplane Flight Manual (AFM) (‘‘the 

temporary revision’’). The procedures listed 

in the temporary revision are required while 

operating with PBV P/N HJ1–13243–101–005 

or P/N HJ1–13243–101–007 installed. This 

insertion and the steps therein may be 

performed by the owner/operator (pilot) 

holding at least a private pilot certificate and 

must be entered into the airplane records 

showing compliance with this AD in 

accordance with 14 CFR 43.9(a)(1)–(4) and 14 

CFR 91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(h) No Reporting Requirement 

Although Honda Service Bulletin SB–420– 

32–001, dated January 8, 2018, and Revision 

B, dated April 16, 2018, specify submitting 

certain information to the manufacturer, this 

AD does not require that action. 

(i) Replace the Power Brake Valve 

As of and at any time after May 29, 2018 

(the effective date retained from AD 2018– 

11–05), if any of the procedures listed in the 

temporary revision referenced in paragraph 

(g) of this AD reveal a leaking PBV, before 

further flight, replace the installed PBV, P/N 

HJ1–13243–101–005 or P/N HJ1–13243–101– 

007, with the improved design PBV, P/N 

HJ1–13243–101–009. The replacement must 

be done using the Accomplishment 

Instructions in either Honda Service Bulletin 

SB–420–32–001, dated January 8, 2018, or 

Revision B, dated April 16, 2018. Before 

further flight after installing P/N HJ1–13243– 

101–009, remove the temporary revision from 

the Honda HA–420 AFM. 

(j) Optional Terminating Action for Inserting 

the AFM Temporary Revision/Pilot Checks 

(1) Instead of inserting the temporary 

revision or at any time after inserting the 

temporary revision required by paragraph (g) 

of this AD and before the mandatory 

replacement required in paragraph (j) of this 

AD, you may replace the installed PBV, P/N 

HJ1–13243–101–005 or P/N HJ1–13243–101– 

007, with the improved design PBV, P/N 

HJ1–13243–101–009. The replacement must 

be done using the Accomplishment 

Instructions in either Honda Service Bulletin 

SB–420–32–001, dated January 8, 2018, or 

Revision B, dated April 16, 2018. Before 

further flight after installing P/N HJ1–13243– 

101–009, remove the temporary revision from 

the Honda HA–420 AFM. 

(2) The on-condition replacement required 

by paragraph (h) of this AD is still required 

before further flight. 

(k) Mandatory Replacement 

Within the next 12 months after the 

effective date of this AD, replace the installed 

PBV, P/N HJ1–13243–101–005 or P/N HJ1– 

13243–101–007, with the improved design 

PBV, P/N HJ1–13243–101–009. The 

replacement must be done using the 

Accomplishment Instructions in either 

Honda Service Bulletin SB–420–32–001, 

dated January 8, 2018, or Revision B, dated 

April 16, 2018. Before further flight after 

installing P/N HJ1–13243–101–009, remove 

the temporary revision from the Honda HA– 

420 AFM. 

(l) Special Flight Permit 

Special flight permits for the AFM 

Limitations portion of this AD are prohibited. 

Special flight permits for the PBV 

replacement required in this AD are 

permitted with the following limitations: One 

ferry flight, including fuel stops, to service 

center with Honda Aircraft Company 

Temporary Revision TR 01.1, dated February 

16, 2018, incorporated into the Honda HA– 

420 AFM. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta ACO 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 manager of the 

certification office, send it to the attention of 

the person identified in paragraph (n) of this 

AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (h) through (j) of this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(n) Related Information 

(1) For more information about this AD, 

contact Samuel Kovitch, Aerospace Engineer, 

Atlanta ACO Branch, FAA, 1701 Columbia 

Avenue, College Park, Georgia 30337; phone: 

(404) 474–5570; fax: (404) 474–5605; email: 

samuel.kovitch@faa.gov. 

(2) For service information identified in 

this AD, contact Honda Aircraft Company 

LLC, 6430 Ballinger Road, Greensboro, North 

Carolina 27410; telephone (336) 662–0246; 

internet: http://www.hondajet.com. FAA, 

Policy and Innovation Division, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on May 

29, 2018. 

Melvin J. Johnson, 

Aircraft Certification Service, Deputy 

Director, Policy and Innovation Division, 

AIR–601. 

[FR Doc. 2018–12127 Filed 6–6–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0504; Product 

Identifier 2018–NM–046–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 707 series 

airplanes and Model 720 and 720B 

series airplanes. This proposed AD was 

prompted by a report indicating that a 

fracture of the midspar fitting resulted 

in the separation of the inboard strut 

and engine from the airplane, and a 

determination that existing inspections 

are not sufficient for timely detection of 

cracking. This proposed AD would 

require repetitive inspections of certain 

nacelle strut spar and overwing fittings, 

and diagonal braces and associated 

fittings; replacement of the diagonal 

brace assembly on certain airplanes; and 

applicable related investigative and 

corrective actions. We are proposing 


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26384 Federal Register / Vol. 83, No. 110 / Thursday, June 7, 2018 / Proposed Rules 

this AD to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by July 23, 2018. 

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 Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster 

Blvd., MC 110–SK57, Seal Beach, CA 

90740–5600; telephone 562–797–1717; 

internet https://

www.myboeingfleet.com. You may view 

this service information at the FAA, 

Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

0504. 

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–2018– 

0504; or in person at Docket Operations 

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

through Friday, except Federal holidays. 

The AD docket contains this NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Chang, Aerospace Engineer, 

Propulsion Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5263; fax: 562–627– 

5210; email: jeffrey.chang@faa.gov or 

George Garrido, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5232; fax: 562–627– 

5210; email george.garrido@faa.gov. 

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– 

2018–0504; Product Identifier 2018– 

NM–046–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

because of those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this NPRM. 

Discussion 

We have received reports of cracking 

of the midspar fittings and of the engine 

and nacelle strut separating from the 

airplane. We issued AD 2012–16–12, 

Amendment 39–16159 (77 FR 49708, 

August 17, 2012) to require inspection 

of the inboard and outboard strut 

midspar fittings and AD 2015–11–04, 

Amendment 39–18167 (80 FR 30605, 

May 29, 2015) to require replacement of 

all engine strut midspar fittings and to 

initiate a life limit program. Since that 

time, we have determined that 

inspections of other strut fittings are 

needed for timely detection of cracking. 

Cracks have been reported in the 

diagonal brace end fittings, forward 

mating fittings, aft mating fittings, 

overwing support fittings, and the upper 

surface and the aft lug(s) of the front 

spar fittings on the nacelle struts, 

numbers 1, 2, 3 and 4. This cracking is 

attributed to fatigue in the end fittings 

and stress corrosion or fatigue in the 

mating fittings. This condition, if not 

addressed, could result in cracks that 

grow beyond a critical length, allowing 

strut fittings to fail and reducing the 

structural integrity of the nacelle. This, 

in combination with damage to adjacent 

attachment structure, could result in the 

loss of an engine from the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information. 

• Boeing 707 Alert Service Bulletin 

A3364, Revision 4, dated February 21, 

2017. The service information describes 

procedures for repetitive detailed 

inspections of the diagonal brace tube 

for any crack; repetitive detailed 

inspections and high frequency eddy 

current (HFEC) inspections of the 

nacelle strut diagonal brace end fittings, 

forward mating fitting, and aft mating 

fitting for any crack; an alternative dye 

penetrant inspection of vertical webs on 

aft mating fitting for any crack; an HFEC 

inspection of the diagonal brace tube for 

any crack; and corrective actions. 

• Boeing 707 Alert Service Bulletin 

A3365, Revision 3, dated March 9, 2017. 

The service information describes 

procedures for repetitive detailed, 

HFEC, and ultrasonic inspections of the 

overwing support fittings for any crack 

at the bolt hole forward of the wing 

front spar and at the holes for the four 

fasteners attaching the fitting to the 

spar, and related investigative and 

corrective actions. 

• Boeing 707 Alert Service Bulletin 

A3514, Revision 1, dated November 9, 

2016. The service information describes 

procedures for repetitive detailed and 

surface HFEC inspections of the front 

spar fittings at nacelle struts numbers 1, 

2, 3, and 4 for cracks, and replacement 

of cracked front spar fittings. 

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 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0504. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

Related investigative actions are followon actions that (1) are related to the 

primary action, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. Corrective 

actions correct or address any condition 

found. Corrective actions in an AD 

could include, for example, repairs. 


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Federal Register / Vol. 83, No. 110 / Thursday, June 7, 2018 / Proposed Rules 26385 

Differences Between This Proposed AD 

and the Service Information 

Boeing 707 Alert Service Bulletin 

A3364, Revision 4, dated February 21, 

2017; Boeing 707 Alert Service Bulletin 

A3365, Revision 3, dated March 9, 2017; 

and Boeing 707 Alert Service Bulletin 

A3514, Revision 1, dated November 9, 

2016; specify to contact the 

manufacturer for certain instructions, 

but this proposed AD would require 

using repair methods, modification 

deviations, replacement deviations, and 

alteration deviations in one of the 

following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 65 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Detailed inspections per Service Bulletin 

A3364, Revision 4.

36 work-hours × $85 per hour = $3,060 

per inspection cycle.

$0 $3,060 per inspection cycle.$198,900 per inspection cycle. 

HFEC inspections per Service Bulletin 

A3364, Revision 4.

128 work-hours × $85 per hour = 

$10,880 per inspection cycle.

0 $10,880 per inspection cycle.$707,200 per inspection cycle. 

Inspections per Service Bulletin A3365, 

Revision 3.

20 work-hours × $85 per hour = $1,700 

per inspection cycle.

0 $1,700 per inspection cycle.$110,500 per inspection cycle. 

Detailed inspections per Service Bulletin 

A3514, Revision 1.

12 work-hours × $85 per hour = $1,020 

per inspection cycle.

0 $1,020 per inspection cycle.$66,300 per inspection cycle. 

HFEC inspections per Service Bulletin 

A3514, Revision 1.

32 work-hours × $85 per hour = $2,720 

per inspection cycle.

0 $2,720 per inspection cycle.$176,800 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

We estimate that any necessary 

proposed replacement of affected 

fittings would take about 96 work-hours 

for a cost of $8,160 per fitting. We have 

received no definitive data on the parts 

costs of the affected fittings. We have no 

way of determining the number of 

aircraft that might need this 

replacement. 

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 and associated 

appliances 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 adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2018–0504; Product Identifier 2018– 

NM–046–AD. 

(a) Comments Due Date 

We must receive comments by July 23, 

2018. 

(b) Affected ADs 

This AD affects AD 82–24–03, Amendment 

39–4496 (47 FR 51099, November 12, 1982) 

(‘‘AD 82–24–03’’) and AD 2005–08–15, 

Amendment 39–14067 (70 FR 21136, April 

25, 2005) (‘‘AD 2005–08–15’’). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 707–100 Long Body, –200, 

–100B Long Body, and –100B Short Body 

series airplanes; Model 707–300, –300B, 

–300C, and –400 series airplanes; and Model 

720 and 720B series airplanes; certificated in 

any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 


sradovich on DSK3GMQ082PROD with PROPOSALS
26386 Federal Register / Vol. 83, No. 110 / Thursday, June 7, 2018 / Proposed Rules 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that a fracture of the midspar 

fitting resulted in the separation of the 

inboard strut and engine from the airplane, 

and a determination that existing inspections 

for other nacelle strut fittings are not 

sufficient for timely detection of cracking. 

We are issuing this AD to address cracks, 

which if not detected and corrected, could 

grow beyond a critical length, allowing the 

strut fitting to fail and reducing the structural 

integrity of the nacelle. This, in combination 

with damage to adjacent attachment 

structure, could result in the loss of an 

engine from the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Detailed Inspections of the 

Front Spar Fittings at Nacelle Struts 

Numbers 1, 2, 3, and 4 

Prior to the accumulation of 3,500 total 

flight hours; within 700 flight hours after the 

most recent inspection specified in Boeing 

707 Alert Service Bulletin A3514, dated July 

29, 2004, was done; or within three months 

after the effective date of this AD; whichever 

occurs later: Do a detailed inspection for 

cracking of the front spar fittings at nacelle 

struts numbers 1, 2, 3, and 4, in accordance 

with the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3514, 

Revision 1, dated November 9, 2016. If any 

cracking is found, before further flight, 

replace the affected fitting, in accordance 

with the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3514, 

Revision 1, dated November 9, 2016. Repeat 

the inspections thereafter at intervals not to 

exceed 700 flight hours. 

(h) Repetitive Surface High Frequency Eddy 

Current (HFEC) Inspections of the Aft Lugs 

on the Front Spar Fittings at Nacelle Struts 

Numbers 1, 2, 3, and 4 

Within 1,500 flight cycles or 48 months 

after the most recent detailed inspection 

required by paragraph (g) of this AD was 

done, whichever occurs first, do a surface 

HFEC inspection for cracking of the aft lugs 

on the front spar fittings at nacelle struts 

numbers 1, 2, 3, and 4, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3514, Revision 1, 

dated November 9, 2016, except as required 

by paragraph (l)(4) of this AD. Do all 

applicable corrective actions before further 

flight. Repeat the inspection thereafter at 

intervals not to exceed 1,500 flight cycles or 

48 months, whichever occurs first. 

(i) Repetitive Inspections of the Overwing 

Support Fitting at Nacelle Struts Numbers 1, 

2, 3, and 4 

At the times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing 707 Alert Service 

Bulletin A3365, Revision 3, dated March 9, 

2017, except as required by paragraph (l)(1) 

of this AD: Do the inspections specified in 

paragraphs (i)(1) through (i)(3) of this AD and 

do all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3365, Revision 3, 

dated March 9, 2017, except as required by 

paragraph (l)(3) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. Repeat the inspections 

thereafter at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3365, Revision 3, 

dated March 9, 2017. 

(1) Do a detailed inspection for any crack 

at all five holes in the overwing support 

fitting, and at the flange radii. 

(2) Do the inspection specified in 

paragraph (i)(2)(i) or (i)(2)(ii) of this AD. 

(i) Do a surface HFEC inspection for any 

crack in the overwing support fitting around 

the hole immediately forward of the spar 

chord, with the bolt in place, and at the 

flange radii. 

(ii) Do an open hole HFEC inspection for 

any crack in the overwing support fitting at 

the hole immediately forward of the spar 

chord. 

(3) Do the inspection specified in 

paragraph (i)(3)(i) or (i)(3)(ii) of this AD. 

(i) Do an ultrasonic inspection for any 

crack in the overwing support fitting around 

the four holes common to the fitting and the 

spar chord, with the bolts in place. 

(ii) Do a surface HFEC inspection for any 

crack in the overwing support fitting around 

the four holes common to the fitting and the 

spar chord, with the bolts in place. 

(j) Inspections of the Nacelle Strut Diagonal 

Braces and Associated Fittings 

For airplanes with nacelle strut diagonal 

braces and associated fittings which have 

accumulated 7,500 flight cycles or more: At 

the applicable times specified in paragraph 

1.E., ‘‘Compliance’’ of Boeing 707 Alert 

Service Bulletin A3364, Revision 4, dated 

February 21, 2017, except as required by 

paragraph (l)(2) of this AD, do the 

inspections specified in paragraphs (j)(1) 

through (j)(3) of this AD. Repeat the 

inspections thereafter at the applicable 

intervals specified in tables 1, 2, 3, and 4 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3364, Revision 4, 

dated February 21, 2017. If any crack is 

found during any inspection required by this 

paragraph, before further flight, do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3364, 

Revision 4, dated February 21, 2017, except 

as required by paragraph (l)(3) of this AD. 

(1) Do a detailed inspection of the nacelle 

strut diagonal brace end fittings, diagonal 

brace tube, forward mating fitting, and aft 

mating fitting for any crack. 

(2) Do HFEC inspections of the nacelle 

strut diagonal brace end fittings, forward 

mating fitting, and aft mating fitting for any 

crack. As an alternative for the aft mating 

fitting, do a dye penetrant inspection of 

vertical webs on aft mating fitting for any 

crack. 

(3) Do an HFEC inspection of the diagonal 

brace tube for any crack. 

(k) Replacement 

For Group 3, 4, and 6 airplanes as 

identified in Boeing 707 Alert Service 

Bulletin A3364, Revision 4, dated February 

21, 2017, on which the outboard diagonal 

brace end fitting (forward or aft) attach holes 

have been oversized as specified in Boeing 

707 Alert Service Bulletin A3364, Revision 4, 

dated February 21, 2017: Within 1,000 flight 

cycles after the effective date of this AD, 

replace the diagonal brace assembly, in 

accordance with Figure 3 of Boeing 707 Alert 

Service Bulletin A3364, Revision 4, dated 

February 21, 2017. 

(l) Exceptions to Service Information 

Specifications 

(1) For purposes of determining 

compliance with the requirements of this AD: 

Where Boeing 707 Alert Service Bulletin 

A3365, Revision 3, dated March 9, 2017, uses 

the phrase ‘‘the Revision 3 date of this 

service bulletin,’’ this AD requires using ‘‘the 

effective date of this AD.’’ 

(2) For purposes of determining 

compliance with the requirements of this AD: 

Where Boeing 707 Alert Service Bulletin 

A3364, Revision 4, dated February 21, 2017, 

uses the phrase ‘‘the Revision 4 date of this 

service bulletin,’’ this AD requires using ‘‘the 

effective date of this AD.’’ 

(3) Where Boeing 707 Alert Service 

Bulletin A3364, Revision 4, dated February 

21, 2017; and Boeing 707 Alert Service 

Bulletin A3365, Revision 3, dated March 9, 

2017; specify contacting Boeing: This AD 

requires repair using a method approved in 

accordance with the procedures specified in 

paragraph (o) of this AD. 

(4) Where Boeing 707 Alert Service 

Bulletin A3514, Revision 1, dated November 

9, 2016, specifies contacting Boeing: This AD 

requires replacement using a method 

approved in accordance with the procedures 

specified in paragraph (o) of this AD. 

(m) Terminating Action for Other ADs 

(1) Accomplishing the initial inspections 

required by paragraph (j) of this AD 

terminates all requirements of AD 82–24–03. 

(2) Accomplishing the initial inspections 

required by paragraph (g) of this AD, 

terminates all requirements of AD 2005–08– 

15. 

(n) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, on any airplane, a front 

spar fitting having a part number other than 

the part numbers specified in paragraph 

2.C.2. of Boeing 707 Alert Service Bulletin 

A3514, Revision 1, dated November 9, 2016. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO 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 manager of the 

certification office, send it to the attention of 

the person(s) identified in paragraph (p)(1) of 

this AD. Information may be emailed to: 9- 

ANM-LAACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 


sradovich on DSK3GMQ082PROD with PROPOSALS
Federal Register / Vol. 83, No. 110 / Thursday, June 7, 2018 / Proposed Rules 26387 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, replacement, or alteration 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO Branch, to make those findings. To be 

approved, the repair method, modification 

deviation, replacement deviation, or 

alteration deviation must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(p) Related Information 

(1) For more information about this AD, 

contact Jeffrey Chang, Aerospace Engineer, 

Propulsion Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5263; fax: 562–627–5210; email: 

jeffrey.chang@faa.gov or George Garrido, 

Aerospace Engineer, Airframe Section, FAA, 

Los Angeles ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5232; fax: 562–627–5210; 

email george.garrido@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet https://

www.myboeingfleet.com. You may view this 

service information at the FAA, Transport 

Standards Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

Issued in Des Moines, Washington, on May 

24, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12128 Filed 6–6–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0517; Product 

Identifier 2017–SW–098–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Airbus 

Helicopters Deutschland GmbH (Airbus 

Helicopters) Model MBB–BK 117 C–2 

and MBB–BK 117 D–2 helicopters. This 

proposed AD would require altering and 

re-identifying the overhead panel shock 

mount assembly (shock mount). This 

proposed AD is prompted by the 

manufacturer’s stress recalculations. 

The actions of this proposed AD are 

intended to correct an unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by August 6, 2018. 

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–2018– 

0517; or in person at Docket Operations 

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

through Friday, except Federal holidays. 

The AD docket contains this proposed 

AD, the European Aviation Safety 

Agency (EASA) AD, the economic 

evaluation, any comments received, and 

other information. The street address for 

Docket Operations (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 rule, 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.helicopters.airbus.com/website/ 

en/ref/Technical-Support_73.html. 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: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Section, Rotorcraft 

Standards Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

matthew.fuller@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 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2017– 

0026, dated February 14, 2017, to 

correct an unsafe condition for Airbus 

Helicopters Model MBB–BK 117 C–2, 

MBB–BK117 C–2e, MBB–BK 117 D–2, 

and MBB–BK117 D–2m helicopters. 

EASA advises that a recent stress 

calculation identified that the shock 

mount may not withstand certification 

crash loads. EASA states that this 

condition, if not corrected, could lead to 

the overhead panel disconnecting 

during an emergency landing and 

injuring occupants. Accordingly, the 

EASA AD requires modifying and reidentifying the shock mounts. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 


sradovich on DSK3GMQ082PROD with PROPOSALS