Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Proposed Rules 31863 

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): 

Bell Helicopter Textron, Inc., Helicopters: 

Docket No. FAA–2008–0288; Directorate 

Identifier 2006–SW–25–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron, 

Inc. (Bell), Model 214B, 214B–1, and 214ST 

helicopters, with pylon support spindle 

assembly (spindle), part number (P/N) 214– 

030–606–005 or –103, installed, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue cracking of a spindle. This condition 

could result in failure of the spindle and 

subsequent loss of control of the helicopter. 

(c) 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. 

(d) Required Actions 

(1) Within 50 hours time-in-service (TIS): 

(i) Create a component history card or 

equivalent record for each spindle, P/N 214– 

030–606–005 and 214–030–606–103, 

recording the spindle’s P/N and serial 

number (S/N). 

(ii) Review the helicopter records to 

determine the hours TIS of each spindle, if 

the hours TIS are not already recorded for 

your model helicopter. For each month for 

which the hours TIS is unknown, record 75 

hours TIS. 

(iii) Determine the total accumulated 

retirement index number (RIN) for each 

spindle. For the purpose of this AD, count 1 

RIN for each takeoff and 2 RIN for each 

external load lift in which the helicopter 

achieves a vertical altitude difference of 

greater than 200 feet indicated altitude 

between the pick-up and drop-off point. For 

any time period for which the accumulated 

RIN cannot be determined while the spindle 

was installed on a helicopter, multiply the 

hours TIS by 30 to calculate the spindle’s 

accumulated RIN. 

(iv) Record the hours TIS and total 

accumulated RIN for each spindle on the 

component history card or equivalent record. 

(2) Revise the Airworthiness Limitations 

section of the applicable maintenance 

manual or Instructions for Continued 

Airworthiness as follows: 

(i) By establishing a new retirement life for 

the spindle, P/N 214–030–606–005, of 1,250 

hours TIS or a total accumulated RIN of 

20,000, whichever occurs first. 

(ii) By reducing the retirement life for the 

spindle, P/N 214–030–606–103, from 5,000 

hours TIS to 2,500 hours TIS or a total 

accumulated RIN of 50,000, whichever 

occurs first. 

(3) Replace any spindle, P/N 214–030– 

606–005, that has been in service for 1,250 

or more hours TIS, or a total accumulated 

RIN of 20,000 or more, whichever occurs 

first. 

(4) Replace any spindle, P/N 214–030– 

606–103, that has been in service for 2,500 

or more hours TIS, or a total accumulated 

RIN of 50,000 or more, whichever occurs 

first. 

(5) Continue to count and record the 

accumulated RIN count and hours TIS for 

each spindle on its component history card 

or equivalent record. 

(e) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Martin Crane, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5056; 

email 7-AVS-ASW-170@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. 

(f) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6330, Transmission Mount. 

Issued in Fort Worth, Texas, on May 17, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–12522 Filed 5–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0454; Directorate 

Identifier 2009–SW–081–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation-Manufactured 

(Sikorsky) Model Helicopters (type 

certificate currently held by Erickson 

Air-Crane Incorporated) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) for 

Sikorsky Aircraft Corporationmanufactured Model S–64E helicopters 

(type certificate currently held by 

Erickson Air-Crane Incorporated 

(Erickson)). That AD currently requires 

inspecting and reworking the main 

gearbox (MGB) assembly second stage 

lower planetary plate (plate). This 

action would establish or reduce the life 

limits for certain flight-critical 

components, remove from service 

various parts, require repetitive 

inspections and other corrective actions, 

and require replacing any cracked part 

discovered during an inspection. This 

proposal is prompted by further analysis 

performed by the current type certificate 

holder and the service history of certain 

parts. The actions specified in the 

proposed AD are intended to prevent a 

crack in a flight critical component, 

failure of a critical part, and subsequent 

loss of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by July 29, 2013. 

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 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, 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 Erickson AirCrane Incorporated, ATTN: Chris 

Erickson/Compliance Officer, 3100 

Willow Springs Rd, PO Box 3247, 

Central Point, OR 97502, telephone 


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31864 Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Proposed Rules 

(541) 664–5544, fax (541) 664–2312, 

email address 

cerickson@ericksonaircrane.com. You 

may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aerospace Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5170; email 7-avsasw-170@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 

On September 5, 1997, we issued AD 

97–19–10, Amendment 39–10130 (62 

FR 47933, September 12, 1997), to 

require, at 1,300 hours time-in-service 

(TIS), a fluorescent-magnetic particle 

inspection of the plate, part number (P/ 

N) 6435–20229–102, for a crack, 

replacing the plate if a crack is found, 

and reworking the plate if there is no 

crack. That action also requires, at 1,500 

hours TIS, and thereafter at intervals not 

to exceed 70 hours TIS, for a reworked 

plate, P/N 6435–20229–102, and for 

plate, P/N 6435–20229–104, inspecting 

for a crack and replacing the main 

gearbox assembly if a crack is found. 

Finally, AD 97–19–10 requires retiring 

these part-numbered plates upon 

reaching 2,600 hours TIS. That action 

was prompted by reports that cracks 

were discovered in four plates, three of 

which had been reworked in accordance 

with previously superseded AD 77–20– 

01, Amendment 39–3045 (42 FR 51565, 

September 29, 1977) and Amendment 

39–3064 (42 FR 56600, October 27, 

1977). The requirements of AD 97–19– 

10 are intended to detect a crack in the 

plate to prevent failure of the plate, 

failure of the main gearbox, and 

subsequent loss of control of the 

helicopter. 

Actions Since Existing AD Was Issued 

Since issuing AD 97–19–10, 

Amendment 39–10130 (62 FR 47933, 

September 12, 1997), Erickson has 

performed a configuration review and 

additional analyses of the safe life for 

various parts and released Erickson 

Service Bulletin (SB) No. 64B General1, Revision 19, dated September 15, 

2010 (SB 64B General-1). SB 64B 

General-1 specifies the retirement life 

for certain parts and assemblies as well 

as noting other maintenance actions. 

This and the previous revisions of SB 

64B General-1 contain reduced or new 

life limits for certain parts, parts which 

should be removed from service, other 

maintenance actions, and various other 

provisions for certain parts. We have 

also reviewed Erickson SB No. 64B10– 

3, Revision D, dated October 15, 2007, 

which provides ultrasonic inspection 

procedures for the Main Rotor (M/R) 

hub horizontal hinge pins. Based on our 

review of this list of parts and 

assemblies, and an analysis of the 

service difficulties, we have determined 

that we need to propose to revise the life 

limit of certain critical parts, remove 

certain parts from service, and require 

additional inspections and other 

maintenance actions of certain parts. 

Failure to establish or revise a life limit 

or remove a part from service when 

there is repeated service difficulties 

with the part could result in failure of 

that part and subsequent loss of control 

of the helicopter. 

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 helicopters of the same 

type design. 

Proposed AD Requirements 

The proposed AD would supersede 

AD 97–19–10 (62 FR 47933, September 

12, 1997) to establish or revise the life 

limit for various parts, to remove 

various parts from service, to require 

various inspections and other 

maintenance actions, and to revise the 

component history card or equivalent 

record and the airworthiness limitations 

section of the maintenance manual 

accordingly. Specifically, we propose, 

before further flight, to establish or to 

revise the retirement life for each of the 

following parts, and to remove from 

service those parts that have reached or 

exceeded the newly established or 

reduced life limit: 

• M/R parts 

Æ Rod and bushing assembly, M/R, P/ 

N 6410–21090–012, –013 or –014; 

Æ Lower plate, M/R hub, P/N 6410– 

23009–102; 

Æ Upper plate, M/R hub, P/N 6410– 

23011–102; 

Æ Swashplate, rotating, M/R, P/N 

6410–24002–101; 

Æ Piston rod, P/N 6410–26005–104; 

Æ Cylinder, damper assembly, P/N 

6410–26215–101; 

Æ M/R blade, P/N 6415–20201–045 or 

–047; 

Æ M/R blade, P/N 6415–20201–048, 

–049, –050, or –051; 

Æ M/R shaft assembly (includes shaft, 

P/N 6435–20078–104), P/N 6435– 

20078–014 or –015; 

Æ M/R shaft assembly (includes shaft, 

P/N 6435–20078–105), P/N 6435– 

20078–016; 

Æ Hub, M/R, P/N S1510–23001–005; 

Æ Spindle assembly, M/R, P/N 

S1510–23027–5; 

Æ Horn assembly, M/R, P/N S1510– 

23350–4, –6, or –8; 

Æ Sleeve, M/R, P/N S1510–23351–2; 

Æ Sleeve lockwasher, M/R, S1510– 

23458–0; 

Æ Cuff, M/R blade, P/N S1515– 

20320–0, –001 or –002; 

Æ Piston assembly, M/R tandem 

servo, P/N S1565–20443–0 or S1565– 

20443–301; 

Æ Fork assembly, M/R tandem servo, 

P/N S1565–20449 or P/N S1565–20449– 

301; 

• Tail Rotor (T/R) parts 

Æ T/R blade, P/N 65160–00001–042, 

–045, or –048; 

Æ T/R blade, P/N 65161–00001–042; 

Æ Bearing, T/R drive shaft, P/N 

SB1111–004 or –601; 

• Main Gearbox parts 

Æ Second stage planetary plate 

assembly, main gearbox assembly, P/N 

6435–20231–012, –014, –015 or –016; 

Æ Oil cooler and support assembly, 

P/N 6435–60050–044; and 

• Other parts 

Æ Truss assembly, stabilizer, P/N 

6420–66250–041. 

In addition to establishing and 

revising the life limit for certain parts, 

we also propose to require, before 

further flight, removing from service the 


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following flight-critical parts due to 

previous service difficulties: 

• Rod and bushing assembly, M/R, 

P/N 6410–21090–011; 

• M/R blade, P/N 6415–20001–013, 

–014, or –015; 

• Pylon stabilizer, P/N 6420–66201– 

010, –014, or –015; 

• M/R shaft assembly, P/N 6435– 

20078–013; 

• Oil cooler and support assembly, 

P/N 6435–60050–043; 

• Pitch change link, rotary rudder, 

P/N 65113–07100–046; and 

• Spindle, M/R blade, P/N S1510– 

23070–3. 

Any part that is required to be removed 

from service is not eligible for 

installation on any helicopter. 

This proposed AD also would also 

require the following inspections and 

other corrective actions: 

• Within 20 hours TIS, and thereafter 

at intervals not to exceed 20 hours TIS, 

inspecting each M/R servo and control 

arm assembly, P/N S1565–20421–10, 

–11, –041, or –043, for any oil leaking 

from the M/R tandem servo housing 

assembly (servo housing), P/N S1565– 

20252–2. If there is any oil leaking from 

the servo housing, before further flight, 

replacing the M/R servo and control arm 

assembly. 

• Within 20 hours TIS or before 

reaching a total of 1,120 hours TIS, 

whichever occurs later, and thereafter at 

intervals not to exceed 200 hours TIS or 

12 months, whichever occurs first, 

performing an ultrasonic inspection 

(UT) of each M/R hub horizontal hinge 

pin, P/N S1510–23099–1 or P/N S1510– 

23099–001, for a crack. 

• Performing a fluorescent-magnetic 

particle inspection (MPI) for a crack: 

Æ In each second stage planetary plate 

assembly, P/N 6435–20231–016, within 

150 hours TIS, or before reaching 1,450 

hours TIS, whichever occurs later; 

Æ In each M/R shaft, P/N 6435– 

20078–104, within 150 hours TIS or 

before reaching 1,450 hours TIS, 

whichever occurs later, and thereafter at 

intervals not to exceed 650 hours TIS; 

Æ In each M/R shaft, P/N 6435– 

20078–105, within 150 hours TIS or 

before reaching 1,450 hours TIS, 

whichever occurs later, and thereafter at 

intervals not to exceed 1,450 hours TIS; 

and 

Æ In each M/R shaft assembly, P/N 

6435–20078–014, –015, or –016, at each 

overhaul of the main gearbox assembly, 

P/N 6435–20400–053, –054, –058, –060, 

–062, –063, –064, –065, or –066. 

• Within 150 hours TIS or before 

reaching 3,375 hours TIS, whichever 

occurs later, and thereafter at intervals 

not to exceed 3,375 hours TIS, 

performing a fluorescent-penetrant 

inspection (FPI) of each housing lug on 

each M/R tandem servo housing 

assembly, P/N S1565–20252–2. 

• If a there is a crack, before further 

flight, replacing the cracked part. 

• At each overhaul of the damper 

assembly, P/N 6410–26200–042, 

replacing certain parts with parts that 

have zero (0) hours TIS. 

Differences Between the Proposed AD 

and the Service Information 

This proposed AD contains only those 

parts for the Model S–64E helicopters 

whose life limit has either been reduced 

or added for an existing P/N, whereas 

SB 64B General-1 also contains parts 

whose life limits have been extended. 

As a result, this proposed AD does not 

include all of the parts or P/Ns that are 

listed in SB 64B General-1. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 13 helicopters of U.S. 

registry, and the proposed actions 

would take the following number of 

estimated work hours to accomplish: 

• 26 work hours (2 work hours per 

helicopter) for the fleet to review the 

helicopter records or to remove a part to 

determine if an affected part is installed; 

• 845 work hours (65 work hours per 

helicopter) for the fleet to replace the 

parts or assemblies on or before 

reaching the retirement lives stated in 

Table 1 of the proposed AD, assuming 

an annual usage of 600 hours TIS; 

• 287 work hours per helicopter to 

replace all the parts or assemblies listed 

in Table 2 of the proposed AD; 

• 130 work hours (10 work hours per 

helicopter) for the fleet to inspect the 

M/R servo housing assemblies for an oil 

leak, assuming each inspection would 

take approximately 0.25 work hour per 

helicopter and would be accomplished 

40 times annually; 

• Approximately 293 work hours 

(22.5 work hours per helicopter) for the 

fleet to UT inspect each M/R hub 

horizontal hinge pin, assuming that 

each inspection would take 7.5 work 

hours per helicopter and would be 

accomplished 3 times annually; 

• 288 work hours (48 work hours per 

helicopter) to perform an MPI of each 

main gearbox second stage lower 

planetary plate and second stage 

planetary plate assembly assuming 6 

helicopters would be inspected 

annually; 

• 192 work hours (32 work hours per 

helicopter) to perform an MPI of each 

M/R shaft and M/R shaft assembly, 

assuming 6 helicopters would be 

inspected annually, and 

• 96 work hours (32 work hours per 

helicopter) to perform an FPI of each 

M/R tandem servo housing assembly, 

assuming 3 helicopters would be 

inspected annually. 

Therefore, we estimate that it would 

take approximately 2,157 work hours to 

accomplish the proposed actions at a 

cost of $183,345, using an average labor 

rate $85 per work hour. Replacement 

parts would cost approximately: 

• $5,363,449 ($412,573 per 

helicopter) to replace the parts or 

assemblies on the entire fleet on or 

before reaching the proposed retirement 

lives, assuming parts for 13 helicopters 

would require replacement; and 

• $2,594,400 per helicopter to replace 

the parts or assemblies that are listed in 

Table 2 of the proposed AD. 

Using these assumptions, the 

estimated total cost for the required 

parts would be approximately 

$7,957,849. Based on these estimated 

amounts using these assumptions, we 

estimate the total cost impact of the 

proposed AD on the U.S. operators 

would be $8,141,194. 

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 

helicopters 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 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 


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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 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 

removing Amendment 39–10130 (62 FR 

47933, September 12, 1997), and adding 

the following new AD: 

Sikorsky Aircraft CorporationManufactured (Sikorsky) Model 

Helicopters (Type Certificate Currently 

Held By Erickson Air-Crane 

Incorporated): Docket No. FAA–2013– 

0454; Directorate Identifier 2009–SW– 

81–AD. 

(a) Applicability 

This AD applies to Sikorsky Model CH– 

54A helicopters, now under the Erickson AirCrane Incorporated (Erickson) Model S–64E 

type certificate, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue cracking in a flight critical 

component, failure of the component, and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 97–19–10, 

Amendment 39–10130 (62 FR 47933, 

September 12, 1997). 

(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, for each part listed 

in Table 1 to paragraph (e) of this AD: 

(i) Remove any part that has reached or 

exceeded its newly established or revised 

retirement life. 

(ii) Record the newly established or revised 

retirement life for each part on the 

component history card or equivalent record. 

(iii) Make pen and ink changes or insert a 

copy of this AD into the Airworthiness 

Limitations section of the maintenance 

manual to establish or revise the retirement 

life for each part that is listed in Table 1 of 

this AD. 

TABLE 1 TO PARAGRAPH (E) OF THIS AD—PARTS WITH NEW OR REVISED LIFE LIMITS

Part name Part number (P/N) Retirement life 

Rod and bushing assembly, main rotor (M/R) ................. 6410–21090–012 ...................................... 5,700 hours time-in-service (TIS) or 60 

months since the initial installation on 

any helicopter, whichever occurs first. 

Rod and bushing assembly, M/R ..................................... 6410–21090–013 or –014 ........................ 5,700 hours TIS. 

Lower plate, M/R hub ....................................................... 6410–23009–102 ...................................... 3,000 hours TIS. 

Upper plate, M/R hub ....................................................... 6410–23011–102 ...................................... 3,000 hours TIS. 

Swashplate, rotating, M/R ................................................ 6410–24002–101 ...................................... 12,860 hours TIS. 

Piston rod .......................................................................... 6410–26005–104 ...................................... 10,500 hours TIS. 

Cylinder, damper assembly .............................................. 6410–26215–101 ...................................... 7,300 hours TIS. 

M/R blade ......................................................................... 6415–20201–045 or –047 ........................ 3,300 hours TIS. 

M/R blade ......................................................................... 6415–20201–048, –049, –050, or –051 ... 20,000 hours TIS. 

Truss assembly, stabilizer ................................................ 6420–66250–041 ...................................... 4,720 hours TIS. 

M/R shaft assembly (includes shaft, P/N 6435–20078– 

104).

6435–20078–014 or –015 ........................ 2,600 hours TIS. 

M/R shaft assembly (includes shaft, P/N 6435–20078– 

105).

6435–20078–016 ...................................... 5,000 hours TIS. 

Second stage planetary plate assembly, main gearbox 

assembly.

6435–20231–012, –014, or –015 ............. 1,300 hours TIS. 

Second stage planetary plate assembly, main gearbox 

assembly.

6435–20231–016 ...................................... 2,600 hours TIS. 

Oil cooler and support assembly ...................................... 6435–60050–044 ...................................... 9,885 hours TIS. 

Tail rotor (T/R) blade ........................................................ 65160–00001–042, –045, or –048 ........... 23,300 hours TIS. 

T/R blade .......................................................................... 65161–00001–042 .................................... 23,300 hours TIS. 

Hub, M/R ........................................................................... S1510–23001–005 .................................... 3,000 hours TIS. 

Spindle assembly, M/R ..................................................... S1510–23027–5 ........................................ 5,675 hours TIS. 

Horn assembly, M/R ......................................................... S1510–23350–4, –6, or –8 ....................... 9,710 hours TIS. 

Sleeve, M/R ...................................................................... S1510–23351–2 ........................................ 12,930 hours TIS. 

Sleeve lockwasher, M/R ................................................... S1510–23458–0 ........................................ 2,700 hours TIS. 

Cuff, M/R blade ................................................................. S1515–20320–0 ........................................ 6,410 hours TIS. 

Cuff, M/R blade ................................................................. S1515–20320–001 or –002 ...................... 12,930 hours TIS. 

Piston assembly, M/R tandem servo ................................ S1565–20443–0 or S1565–20443–301 .... 8,100 hours TIS. 

Fork assembly, M/R tandem servo ................................... S1565–20449 or S1565–20449–301 ........ 8,100 hours TIS. 

Bearing, T/R drive shaft .................................................... SB1111–004 or –601 ................................ 1,000 hours TIS or 12 months while installed on any helicopter, whichever occurs first. 

Note to Table 1 to paragraph (e) of this 

AD: The list of parts in Table 1 to paragraph 

(e) of this AD contains only a portion of the 

life-limited parts for this model helicopter 

and is not an all-inclusive list. 

(2) Before further flight, remove from 

service any part with a P/N listed in Table 

2 to Paragraph (e) of this AD, regardless of 


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the part’s TIS. The part numbers listed in 

Table 2 to paragraph (e)(2) of this AD are not 

eligible for installation on any helicopter. 

TABLE 2 TO PARAGRAPH (e) OF THIS

AD—PARTS TO BE REMOVED FROM

SERVICE

Part name P/N 

Rod and bushing assembly, M/R.6410–21090– 

011 

M/R blade .......................... 6415–20001– 

013, –014, or 

–015 

Pylon stabilizer .................. 6420–66201– 

010, –014, or 

–015 

M/R shaft assembly ........... 6435–20078– 

013 

Oil cooler and support assembly.6435–60050– 

043 

Pitch change link, rotary 

rudder.

65113–07100– 

046 

Spindle, M/R blade ............ S1510–23070–3 

(3) Within 20 hours TIS, and thereafter at 

intervals not to exceed 20 hours TIS, visually 

inspect each M/R servo and control arm 

assembly, P/N S1565–20421–10, –11, –041, 

or –043, and determine if there is any oil 

leaking from the M/R tandem servo housing 

assembly (servo housing), P/N S1565–20252– 

2. If there is any oil leaking from the servo 

housing, before further flight, replace the M/ 

R servo and control arm assembly. 

(4) Within 20 hours TIS or before reaching 

1,120 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 200 hours 

TIS or 12 months, whichever occurs first, 

ultrasonic (UT) inspect each M/R hub 

horizontal hinge pin (hinge pin), P/N S1510– 

23099–1 or P/N S1510–23099–001, for a 

crack in accordance with the 

Accomplishment Instructions, paragraphs 

2.A through 2.C, of Erickson Service Bulletin 

(SB) No. 64B10–3, Revision D, dated October 

15, 2007, except you are not required to 

contact Erickson nor send hinge pins to 

them. A non-destructive testing (NDT) UT 

Level I Special, Level II, or Level III inspector 

who is qualified under the guidelines 

established by ASNT SNT–TC–1A, ISO 9712, 

or an FAA-accepted equivalent qualification 

standard for NDT inspection and evaluation, 

must perform the UT inspection. 

(5) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, 

perform a fluorescent-magnetic particle 

inspection (MPI) of each second stage 

planetary plate assembly, P/N 6435–20231– 

016, for a crack. 

(6) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 650 hours 

TIS, perform an MPI of each M/R shaft, 

P/N 6435–20078–104, for a crack, paying 

particular attention to the lower spline area. 

(7) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 1,450 

hours TIS, perform an MPI of each M/R shaft, 

P/N 6435–20078–105, for a crack, paying 

particular attention to the lower spline area. 

(8) Within 150 hours TIS or before reaching 

3,375 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 3,375 

hours TIS, perform a fluorescent penetrant 

inspection of each housing lug on each servo 

housing, P/N S1565–20252–2, for a crack. 

(9) At each overhaul of the main gearbox 

assembly, P/N 6435–20400–053, –054, –058, 

–060, –062, –063, –064, –065, or –066, 

perform an MPI of the entire shaft of each 

M/R shaft assembly, P/N 6435–20078–014, 

–015, or –016, for a crack, paying particular 

attention to the rotating swashplate spherical 

bearing ball travel area, which is located 

approximately ten inches above the upper 

roller bearing journal shoulder. 

(10) If there is a crack in any part, before 

further flight, replace the cracked part. 

(11) At each overhaul of the damper 

assembly, P/N 6410–26200–042, replace the 

following parts with airworthy parts that 

have zero (0) hours TIS: 

(i) All Air Force-Navy Aeronautical 

Standard (AN), Aerospace Standard (AS), 

Military Standard (MS), and National 

Aerospace Standard (NAS) nuts, bolts, 

washers, and packings, except packing, P/N 

MS28775–011, installed on stud, P/N 

SHF111–11SN–12A; 

(ii) Lock washer, P/N SS5073–2; 

(iii) Nut, P/N SS5081–05; 

(iv) Felt seal, P/N S1510–26017; 

(v) Retaining ring, P/N UR106L; and 

(vi) Nut, P/N 6410–26214–101. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aerospace Engineer, Rotorcraft Certification 

Office, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5170; email 7-avs-asw170@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. 

(g) Additional Information 

Erickson Service Bulletin (SB) No. 64B 

General-1, Revision 19, dated September 15, 

2010, which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information 

identified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson/ 

Compliance Officer, 3100 Willow Springs Rd, 

PO Box 3247, Central Point, OR 97502, 

telephone (541) 664–5544, fax (541) 664– 

2312, email address 

cerickson@ericksonaircrane.com. You may 

review a copy of this information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200: Main Rotor System; 6300: Main 

Rotor Drive System; 6410: Tail Rotor Blades; 

6500: Tail Rotor Drive System. 

Issued in Fort Worth, Texas, on May 17, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–12523 Filed 5–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0425; Directorate 

Identifier 2012–NM–224–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 certain 

The Boeing Company Model 747 

airplanes. This proposed AD was 

prompted by reports of cracking in the 

forward and aft inner chord of the body 

station (BS) 2598 bulkhead near the 

upper corners of the cutout for the 

horizontal stabilizer rear spar, and 

cracking in the bulkhead upper and 

lower web panels near the inner chord 

to shear deck connection. This proposed 

AD would require doing repetitive 

inspections for cracking in the bulkhead 

splice fitting, frame supports, forward 

and aft inner chords, and floor support; 

doing an inspection for cracking in the 

bulkhead upper web, doubler, and 

bulkhead lower web; and corrective 

actions if necessary; for certain 

airplanes, inspections for cracking in 

the repaired area of the bulkhead, and 

corrective actions if necessary; for 

certain airplanes, support frame 

modification and support frame 

inspections, and related investigative 

and corrective actions, if necessary; for 

certain airplanes, repetitive support 

frame post-modification inspections and 

inspections for cracking in the hinge 

support, and related investigative and 

corrective actions if necessary; for 

certain airplanes, a one-time inspection 

of the frame web and upper shear deck 

(floor support) chord aft side for 

fasteners; and a one-time inspection of 

the upper forward inner chord, frame 

support fitting and splice fitting, for the 

installation of certain fasteners; and 

related investigative and corrective 

actions if necessary; for certain 

airplanes, a one-time inspection of the 

upper forward inner chord, frame 


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