Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations 46543 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0375; Directorate 

Identifier 2007–NM–272–AD; Amendment 

39–15627; AD 2008–16–09] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers Model SD3–60 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding two 

existing airworthiness directives (ADs), 

which apply to all Short Brothers Model 

SD3–60 airplanes. One of the ADs 

currently requires inspection of the 

welded joints of the balance weight 

brackets for the elevator trim tabs for 

cracking; repetitive inspections, as 

applicable; and corrective actions 

including the eventual replacement of 

all brackets. The other AD currently 

requires, for certain airplanes, repetitive 

inspections for cracking of the balance 

weight brackets and replacement of any 

cracked bracket, and provides for an 

optional terminating action for the 

repetitive inspections. This new AD 

requires an additional inspection to 

detect cracks of the balance weight 

brackets, applicable related investigative 

and corrective actions, and replacement 

of a certain balance weight bracket 

when it has reached its maximum life 

limit. This AD results from a report 

indicating that several reworked balance 

weight brackets have exhibited signs of 

premature failure. We are issuing this 

AD to prevent failure of the balance 

weight brackets of the elevator trim tabs, 

which could cause loss of the balance 

weight. This could result in incorrect 

trim during takeoff and landing, and 

reduced controllability of the airplane. 

DATES: This AD becomes effective 

September 15, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 15, 2008. 

On March 14, 2005 (70 FR 9212, 

February 25, 2005), the Director of the 

Federal Register approved the 

incorporation by reference of Short 

Brothers Alert Service Bulletin SD360–

55–A21, dated December 16, 2004. 

On August 3, 2004 (69 FR 38813, June 

29, 2004), the Director of the Federal 

Register approved the incorporation by 

reference of Short Brothers Service 

Bulletin SD360–55–20, dated June 26, 

2003. 

ADDRESSES: For service information 

identified in this AD, contact Short 

Brothers, Airworthiness & Engineering 

Quality, P.O. Box 241, Airport Road, 

Belfast BT3 9DZ, Northern Ireland. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2004–13–08, amendment 

39–13690 (69 FR 38813, June 29, 2004); 

and AD 2005–04–13, amendment 39–

13985 (70 FR 9212, February 25, 2005). 

The existing ADs apply to all Short 

Brothers Model SD3–60 airplanes. That 

NPRM was published in the Federal 

Register on April 1, 2008 (73 FR 17260). 

That NPRM proposed to retain the 

requirements of the existing ADs. That 

NPRM also proposed to require an 

additional inspection to detect cracks of 

the balance weight brackets, applicable 

related investigative and corrective 

actions, and replacement of a certain 

balance weight bracket when it has 

reached its maximum life limit. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Inspections (required by AD 

2004–13–08).

12 $80 (1) $960, per inspection cycle 21 $20,160, per inspection cycle. 

Replacement (required by 

AD 2004–13–08).

8 80 $632 $1,272 ............................... 21 $26,712. 

Inspections (required by AD 

2005–04–13).

12 80 (1) $960, per inspection cycle 21 $20,160, per inspection cycle. 

Inspection (new required 

action).

12 80 (1) $960, per inspection cycle 21 $20,160, per inspection cycle. 

Replacement (new required 

action).

8 80 864 $1,504, per replacement 

cycle.

21 $31,584, per replacement cycle. 

1 None. 


jlentini on PROD1PC65 with RULES
46544 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations 

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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendments 39–13690 (69 

FR 38813, June 29, 2004), and 39–13985 

(70 FR 9212, February 25, 2005), and by 

adding the following new airworthiness 

directive (AD): 

2008–16–09 Short Brothers PLC: 

Amendment 39–15627. Docket No. 

FAA–2008–0375; Directorate Identifier 

2007–NM–272–AD. 

Effective Date 

(a) This AD becomes effective September 

15, 2008. 

Affected ADs 

(b) This AD supersedes ADs 2004–13–08 

and 2005–04–13. 

Applicability 

(c) This AD applies to all Short Brothers 

Model SD3–60 airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from a report indicating 

that several reworked balance weight 

brackets have exhibited signs of premature 

failure. We are issuing this AD to prevent 

failure of the balance weight bracket of the 

elevator trim tab, which could cause loss of 

the balance weight. This could result in 

incorrect trim during takeoff and landing, 

and reduced controllability of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2004–13–08 

Service Bulletin Reference 

(f) The term ‘‘service bulletin,’’ as used in 

paragraphs (g) through (j) of this AD, means 

the Accomplishment Instructions of Short 

Brothers Service Bulletin SD360–55–20, 

dated June 26, 2003; or Revision 1, dated 

June 20, 2005. 

Initial Inspection 

(g) Within 2 months after August 3, 2004 

(the effective date of AD 2004–13–08): Do a 

dye penetrant inspection for cracking in the 

welded joints of the balance weight brackets 

for the left and right elevator trim tabs, in 

accordance with the service bulletin. 

Investigative and Corrective Actions if No 

Cracking Is Found 

(h) If no cracking is found during the 

inspection required by paragraph (g) of this 

AD, do the actions required by paragraphs 

(h)(1) and (h)(2) of this AD at the applicable 

compliance times. 

(1) Repeat the inspection required by 

paragraph (g) of this AD at intervals not to 

exceed 4,800 flight hours until the bracket is 

replaced per paragraph (h)(2) or (i) of this 

AD. 

(2) Prior to the accumulation of 28,800 

total flight hours, or within 6 months after 

August 3, 2004, whichever occurs later: 

Replace any bracket that has not been 

replaced per paragraph (i) of this AD with a 

new bracket or with a serviceable bracket that 

has been inspected in accordance with 

paragraph (g) of this AD. Replace in 

accordance with the service bulletin. 

Replacement of the brackets constitutes 

terminating action for the repetitive 

inspections required by paragraph (h)(1) of 

this AD. 

Corrective Actions if Any Cracking Is Found 

(i) If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, accomplish the 

applicable action in paragraph (i)(1) or (i)(2) 

of this AD in accordance with the service 

bulletin. 

(1) For airplanes that have accumulated 

less than 28,800 flight hours and on which 

all cracking on brackets is less than 0.25 inch 

in length: Repair the affected bracket in 

accordance with part B of the service bulletin 

(including the additional dye penetrant 

inspection of the repaired welded joint) and 

repeat the inspection required by paragraph 

(g) of this AD at intervals not to exceed 4,800 

flight hours; or replace the bracket in 

accordance with paragraph (h)(2) of this AD. 

Replacement of the bracket constitutes 

terminating action for the repetitive 

inspections. 

(2) For any airplane on which any cracking 

on a bracket is 0.25 inch in length or greater, 

and for any airplane that has accumulated 

28,800 flight hours or more on which any 

cracking of any length is found on a bracket: 

Replace the affected bracket with a new 

bracket or with a serviceable bracket that has 

been inspected in accordance with paragraph 

(g) of this AD. Replacement of the bracket 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(i)(1) of this AD. 

Refitting 

(j) Before further flight following any 

inspection per paragraph (g) or (h) of this AD; 

or before further flight following repair or 

replacement of a bracket per paragraph (h)(2) 

or (i) of this AD: Refit the balance weights, 

covers, and trim tabs, in accordance with the 

service bulletin. Where the service bulletin 

specifies to contact the manufacturer for 

disposition of certain conditions while 

refitting, obtain further disposition 

instructions from the Manager, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Parts Installation 

(k) As of August 3, 2004, no person may 

install on any airplane a balance weight 

bracket unless the welded joint has been 

inspected in accordance with paragraph (g) of 

this AD. 

Requirements of AD 2005–04–13 

Service Bulletin Reference 

(l) The following information applies to the 

service bulletin referenced in paragraphs (l) 

through (o) of this AD: 

(1) The term ‘‘service bulletin,’’ as used in 

paragraphs (l) through (o) of this AD, means 


jlentini on PROD1PC65 with RULES
Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations 46545 

the Accomplishment Instructions of Short 

Brothers Alert Service Bulletin SD360–55–

A21, dated December 16, 2004. 

(2) Although the service bulletin specifies 

to return subject parts to the manufacturer, 

this AD does not include that requirement. 

Repetitive Inspections 

(m) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–07–6011xA, and 

having a serial number beginning with ‘‘X3’’

or ‘‘X4’’: Prior to the accumulation of 250 

flight hours since installation of the subject 

balance weight bracket of the elevator trim 

tab, or within 30 flight hours after March 14, 

2005 (the effective date of AD 2005–04–13), 

whichever is later, do a dye penetrant 

inspection for cracking of the balance weight 

brackets for the left and right elevator trim 

tabs, in accordance with the service bulletin. 

(1) For a balance weight bracket on which 

no cracking is found: Do paragraph (o) of this 

AD, and repeat the inspection thereafter at 

intervals not to exceed 250 flight hours until 

paragraph (n) of this AD is accomplished. 

(2) For a balance weight bracket on which 

any cracking is found: Before further flight, 

replace the bracket with a new or reworked 

balance weight bracket that conforms to the 

approved design standard in accordance with 

the service bulletin, and do paragraph (o) of 

this AD. 

Optional Terminating Action 

(n) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–07–6011xA, and 

having a serial number beginning with ‘‘X3’’

or ‘‘X4’’: Replacement of any subject balance 

weight bracket with a new or reworked 

balance weight bracket that conforms to the 

approved design standard, in accordance 

with the service bulletin, constitutes 

terminating action for the repetitive 

inspections required by paragraph (m) of this 

AD for the replaced bracket. 

Refitting 

(o) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–07–6011xA, and 

having a serial number beginning with ‘‘X3’’

or ‘‘X4’’: Before further flight following any 

inspection or replacement of a bracket in 

accordance with paragraphs (m) and (n) of 

this AD: Refit the balance weights, covers, 

and trim tabs, in accordance with the service 

bulletin. Where the service bulletin specifies 

to contact the manufacturer for disposition of 

certain conditions while refitting, obtain 

further disposition instructions from the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

Parts Installation 

(p) For all airplanes: As of March 14, 2005, 

no person may install, on any airplane 

subject to this AD, a balance weight bracket 

having part number SD3–07–6011xA, and 

having a serial number beginning with ‘‘X3’’

or ‘‘X4,’’ unless the bracket is also marked 

‘‘Rework batch number R–Bxxxxx’’ (where 

‘‘xxxxx’’ is a number). 

New Requirements of This AD 

Inspection(s) and Replacements 

(q) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–07–6011xA 

manufactured in the year 2003 or 2004, 

including reworked brackets, installed in 

accordance with paragraph (h)(2), (i)(2), or 

(n) of this AD, as applicable: Do the actions 

specified in paragraphs (q)(1) and (q)(2) of 

this AD in accordance with Parts A and B of 

the Accomplishment Instructions of Shorts 

Alert Service Bulletin SD360–55–A21, 

Revision 1, dated March 29, 2007. 

(1) Within 30 flight hours after the effective 

date of this AD, or within 250 flight hours 

since installation of the balance weight 

brackets of the elevator trim tabs or since the 

last inspection required by paragraph (g), 

(h)(1), (i)(1), or (m) of this AD, whichever 

occurs later: Do a dye penetrant inspection to 

detect cracks of the balance weight brackets 

of the elevator trim tabs. 

(i) If no crack is detected, repeat the dye 

penetrant inspection at intervals not to 

exceed 250 flight hours, until the 

replacement required by paragraph (q)(2) of 

this AD is done. 

(ii) If any crack is detected, before further 

flight, do the replacement specified in 

paragraph (q)(2) of this AD. 

(2) Before the accumulation of 1,750 flight 

hours since installation of the balance weight 

brackets of the elevator trim tabs, or within 

180 days after the effective date of this AD, 

whichever occurs later: Replace the balance 

weight brackets with new balance weight 

brackets manufactured in 2005 or later. 

Thereafter, replace any balance weight 

bracket with a new bracket manufactured in 

2005 or later at intervals not to exceed the 

accumulation of 1,750 flight hours on that 

bracket. Accomplishment of the initial 

replacement ends the repetitive inspection 

requirements of this AD. 

(r) For airplanes equipped with balance 

weight brackets of the elevator trim tabs 

having part number SD3–31–6213xB 

inspected in accordance with paragraph (g), 

(h)(1), or (i)(1) of this AD and retained or 

refitted following approved repair in 

accordance with paragraph (j) of this AD: Do 

the actions specified in paragraphs (r)(1) and 

(r)(2) of this AD in accordance with Parts A 

and B of the Accomplishment Instructions of 

Shorts Service Bulletin SD360–55–20, 

Revision 2, dated March 29, 2007. 

(1) Within 4,800 flight hours since last 

inspection, or within 180 days after the 

effective date of this AD, whichever occurs 

later, and thereafter at intervals not to exceed 

4,800 flight hours: Do a dye penetrant 

inspection to detect cracks of the balance 

weight brackets of the elevator trim tabs. 

(i) If no crack is detected, repeat the dye 

penetrant inspection at intervals not to 

exceed 4,800 flight hours, until the 

replacement required by paragraph (r)(2) of 

this AD is done. 

(ii) If any crack is detected, before further 

flight, do the replacement specified in 

paragraph (r)(2) of this AD. 

(2) Before the accumulation of 28,800 flight 

hours since any balance weight bracket of the 

elevator trim tabs is new, or within 180 days 

after the effective date of this AD, whichever 

occurs later: Replace the balance weight 

brackets with new balance weight brackets 

manufactured in 2005 or later. Thereafter, 

replace any balance weight bracket with a 

new bracket manufactured in 2005 or later at 

intervals not to exceed the accumulation of 

28,800 flight hours on that bracket. 

Accomplishment of the initial replacement 

ends the repetitive inspection requirements 

of this AD. 

Part Installation 

(s) For all airplanes: As of the effective date 

of this AD, no person may install, on any 

airplane, a balance weight bracket of the 

elevator trim tab manufactured earlier than 

2005. 

Alternative Methods of Compliance (AMOCs) 

(t) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Todd Thompson, Aerospace 

Engineer, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; telephone (425) 227–1175; fax 

(425) 227–1149. Before using any approved 

AMOC on any airplane to which the AMOC 

applies, notify your appropriate principal 

inspector (PI) in the FAA Flight Standards 

District Office (FSDO), or lacking a PI, your 

local FSDO. 

Related Information 

(u) European Aviation Safety Agency 

emergency airworthiness directive 2007–

0107–E, dated April 18, 2007, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(v) You must use the service bulletins 

specified in Table 1 of this AD to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision level Date 

Short Brothers Alert Service Bulletin SD360–55–A21 .............................................................................. Original ............... December 16, 2004. 

Short Brothers Service Bulletin SD360–55–20 ......................................................................................... Original ............... June 26, 2003. 

Shorts Alert Service Bulletin SD360–55–A21 ........................................................................................... Revision 1 ........... March 29, 2007. 

Shorts Service Bulletin SD360–55–20 ...................................................................................................... Revision 1 ........... June 20, 2005. 


jlentini on PROD1PC65 with RULES
46546 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE—Continued 

Service Bulletin Revision level Date 

Shorts Service Bulletin SD360–55–20 ...................................................................................................... Revision 2 ........... March 29, 2007. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Shorts Alert Service Bulletin SD360–55–A21, 

Revision 1, dated March 29, 2007; Shorts 

Service Bulletin SD360–55–20, Revision 1, 

dated June 20, 2005; and Shorts Alert Service 

Bulletin SD360–55–20, Revision 2, dated 

March 29, 2007; in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On March 14, 2005 (70 FR 9212, 

February 25, 2005), the Director of the 

Federal Register approved the incorporation 

by reference of Short Brothers Alert Service 

Bulletin SD360–55–A21, dated December 16, 

2004. 

(3) On August 3, 2004 (69 FR 38813, June 

29, 2004), the Director of the Federal Register 

approved the incorporation by reference of 

Short Brothers Service Bulletin SD360–55–

20, dated June 26, 2003. 

(4) Contact Short Brothers, Airworthiness & 

Engineering Quality, P.O. Box 241, Airport 

Road, Belfast BT3 9DZ, Northern Ireland, for 

a copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on July 23, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–17744 Filed 8–8–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0450; Directorate 

Identifier 2007–SW–39–AD; Amendment 39–

15634; AD 2008–16–16] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (BHTC) 

Model 230 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for BHTC 

Model 230 helicopters. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

Canada which indicates that the existing 

rigging procedures for the tail rotor 

pitch change mechanism have to be 

changed due to the possibility of parts 

interference. The cumulative effect of 

individual part tolerances resulting in 

the total assemblage of those parts being 

out of tolerance could result in the tail 

rotor yoke striking another part other 

than the flapping stop (parts 

interference) as cited in the MCAI. Also, 

the misalignment of the tail rotor 

counterweight bellcrank may result in 

higher tail rotor pedal forces and a 

higher pilot workload after failure of the 

No. 1 hydraulic system. Both parts 

interference and the misaligned 

counterweight bellcrank create an 

unsafe condition. This AD requires 

actions that are intended to address 

these unsafe conditions. 

DATES: This AD becomes effective on 

September 15, 2008. 

The incorporation by reference of 

certain publications is approved by the 

Director of the Federal Register as of 

September 15, 2008. 

ADDRESSES: You may examine the AD 

docket on the Internet at 

http://www.regulations.gov or in person 

at the Docket Operations office, U.S. 

Department of Transportation, M–30, 

West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC between 9 a.m. and 5 

p.m. Monday through Friday, except 

Federal holidays. 

You may get the service information 

identified in this AD from Bell 

Helicopter Textron Canada, 12,800 Rue 

de l’Avenir, Mirabel, Quebec J7J1R4, 

telephone (450) 437–2862 or (800) 363–

8023, fax (450) 433–0272. 

Examining the Ad Docket: The AD 

docket contains the Notice of proposed 

rulemaking (NPRM), the economic 

evaluation, any comments received, and 

other information. The street address 

and operating hours for the Docket 

Operations office (telephone (800) 647–

5527) are in the ADDRESSES section of 

this AD. Comments will be available in 

the AD docket shortly after they are 

received. 

FOR FURTHER INFORMATION CONTACT: 

Tyrone Millard, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Standards Staff, Fort Worth, 

Texas 76193–0111, telephone (817) 

222–5439, fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to the BHTC Model 230 

helicopters on April 14, 2008. That 

NPRM was published in the Federal 

Register on April 23, 2008 (73 FR 

21855). That NPRM proposed to require, 

within the next 150 hours time-inservice (TIS) or at the next annual 

inspection, whichever occurs first, 

adjusting the rigging of the tail rotor 

pitch change mechanism, and if a gap 

exists between the tail rotor yoke and 

the flapping stop, replacing the tail rotor 

yoke with an airworthy tail rotor yoke. 

If no gap exists between the tail rotor 

yoke and the flapping stop at either full 

right or full left pedal position, 

adjusting the tail rotor pitch change 

mechanism and the tail rotor pedal 

forces was proposed. 

Comments 

By publishing the NPRM, we gave the 

public an opportunity to participate in 

developing this AD. However, we 

received no comment on the NPRM or 

on our determination of the cost to the 

public. Therefore, based on our review 

and evaluation of the available data, we 

have determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Related Service Information 

Bell Helicopter Textron has issued 

Alert Service Bulletin 230–07–36, dated 

January 9, 2007. The actions described 

in the MCAI are intended to correct the 

same unsafe condition as that identified 

in the service information. 

Differences Between This AD and the 

MCAI 

The compliance times in this AD 

differ from the MCAI in that compliance 

is required within the next 150 hours 

TIS or at the next annual inspection, 

whichever occurs first, instead of ‘‘at the 

next 150 hour or annual inspection but 

no later than 31 December 2007.’’

Costs of Compliance 

We estimate that this AD will affect 

about 20 helicopters of U.S. registry. We 

also estimate that it will take 2 workhours per helicopter to adjust the 


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