Federal Register / Vol. 75, No. 59 / Monday, March 29, 2010 / Rules and Regulations 15331 

TABLE 1—APPLICABILITY

Boeing Service Bulletin Revision Dated Applicable model/series 

757–35A0015 ............................................ 2 June 15, 2000 ........................................... 757–200, 757–200CB, 757–200PF. 

757–35A0016 ............................................ 1 June 15, 2000 ........................................... 757–300. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 35: Oxygen. 

Unsafe Condition 

(e) This AD results from reports of a lowpressure flex-hose of a flightcrew oxygen 

system that burned through due to 

inadvertent electrical current from a short 

circuit in an adjacent audio select panel. We 

are issuing this AD to prevent inadvertent 

electrical current which can cause the lowpressure flex-hoses used in the flightcrew 

and supernumerary oxygen system to melt or 

burn, resulting in oxygen system leakage and 

smoke or fire. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection 

(g) Within 36 months after the effective 

date of this AD, inspect to determine whether 

any low-pressure flex-hose of the flightcrew 

and supernumerary oxygen systems installed 

under the oxygen mask stowage location has 

a part number identified in Table 2 of this 

AD. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the lowpressure flex-hoses of the flightcrew and 

supernumerary oxygen system can be 

conclusively determined from that review. 

(1) For any low-pressure flex-hose having 

a part number identified in Table 2 of this 

AD, before further flight, replace the hose 

with a new or serviceable part, in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin identified in Table 

1 of this AD. Recording the part number of 

the hose being replaced is not required by 

this AD. 

(2) For any low-pressure flex-hose not 

having a part number identified in Table 2 

of this AD, no further action is required by 

this paragraph. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install a flightcrew or 

supernumerary oxygen hose with a part 

number identified in Table 2 of this AD on 

any airplane. 

TABLE 2—APPLICABLE PART NUMBERS

Boeing specification part 

No.— 

Equivalent Boeing supplier part numbers— 

Sierra Engineering Spencer Fluid Puritan Bennett Hydraflow 

AVOX 

(formerly Sierra 

Engineering) 

60B50059–70 ........................ 835–01–70 9513–20S5–18.0 ZH784–20 ............................. 38001–70 9513–835–01–70 

60B50059–81 ........................ 835–01–81 9513–20S5–24.0 ZH784–81 ............................. 38001–81 9513–835–01–81 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(i) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Alert Service Bulletin 757–35A0015, 

dated September 2, 1999, or Revision 1, 

dated November 11, 1999; or Boeing Alert 

Service Bulletin 757–35A0016, dated 

November 11, 1999; are considered 

acceptable for compliance with the 

corresponding actions specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: 

Nicholas Wilson, Aerospace Engineer, Cabin 

Safety and Environmental Systems Branch, 

ANM–150S, FAA, Seattle ACO, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6476; fax (425) 

917–6590. Or, e-mail information to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Service Bulletin 

757–35A0015, Revision 2, dated June 15, 

2000; or Boeing Service Bulletin 757– 

35A0016, Revision 1, dated June 15, 2000; as 

applicable; to do the actions required by this 

AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 9, 

2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5857 Filed 3–26–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0556; Directorate 

Identifier 2007–NM–028–AD; Amendment 

39–16246; AD 2010–07–02] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Aircraft Equipped With Honeywell 

Primus II RNZ–850( )/–851( ) 

Integrated Navigation Units 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


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15332 Federal Register / Vol. 75, No. 59 / Monday, March 29, 2010 / Rules and Regulations 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to certain Honeywell 

Primus II RNZ–850( )/–851( ) 

integrated navigation units (INUs). As 

one alternative for compliance, the 

existing AD provides for a one-time 

inspection to determine whether a 

certain modification has been installed 

on the Honeywell Primus II NV–850 

navigation receiver module (NRM), 

which is part of the INU. In lieu of 

accomplishing this inspection, and for 

aircraft found to have an affected NRM, 

that AD provides for revising the aircraft 

flight manual to include new limitations 

for instrument landing system 

approaches. That AD also requires an 

inspection to determine whether certain 

other modifications have been done on 

the NRM; and doing related 

investigative, corrective, and other 

specified actions, as applicable; as well 

as further modifications to address 

additional anomalies. This AD extends 

the compliance time for a certain 

inspection and associated actions. This 

AD also revises the applicability to 

include additional affected INUs. This 

AD results from reports indicating that 

erroneous localizer and glideslope 

indications have occurred on certain 

aircraft equipped with the subject INUs. 

We are issuing this AD to ensure that 

the flightcrew has accurate localizer and 

glideslope deviation indications. An 

erroneous localizer or glideslope 

deviation indication could lead to the 

aircraft making an approach off the 

localizer, which could result in impact 

with an obstacle or terrain. 

DATES: This AD becomes effective May 

3, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 3, 2010. 

On December 1, 2006 (71 FR 62907, 

October 27, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of Honeywell 

Alert Service Bulletin 7510100–34– 

A0035, dated July 11, 2003; and 

Honeywell Service Bulletin 7510100– 

34–0037, dated July 8, 2004. 

ADDRESSES: For service information 

identified in this AD, contact Honeywell 

Aerospace, Technical Publications and 

Distribution, M/S 2101–201, P.O. Box 

52170, Phoenix, Arizona 85072–2170; 

telephone 602–365–5535; fax 602–365– 

5577; Internet http:// 

www.honeywell.com. 

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: 

Daniel Bui, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130L, FAA, Los Angeles Aircraft 

Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 

90712–4137; telephone (562) 627–5339; 

fax (562) 627–5210. 

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 2006–22–05, 

Amendment 39–14802 (71 FR 62907, 

October 27, 2006). The existing AD 

applies to various aircraft equipped 

with certain Honeywell Primus II RNZ– 

850( )/–851( ) integrated navigation 

units (INUs). That NPRM was published 

in the Federal Register on May 19, 2008 

(73 FR 28751). That NPRM proposed to 

continue to provide, as one alternative 

for compliance, a one-time inspection to 

determine whether a certain 

modification has been installed on the 

Honeywell Primus II NV–850 navigation 

receiver module (NRM), which is part of 

the INU. In lieu of accomplishing this 

inspection, and for aircraft found to 

have an affected NRM, that NPRM 

proposed to continue to provide for 

revising the aircraft flight manual to 

include new limitations for instrument 

landing system approaches. That NPRM 

proposed to continue to require an 

inspection to determine whether certain 

other modifications have been done on 

the NRM; and doing related 

investigative, corrective, and other 

specified actions, as applicable; as well 

as further modifications to address 

additional anomalies. That NPRM also 

proposed to extend the compliance time 

for a certain inspection and associated 

actions and to revise the applicability to 

include additional affected INUs. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request for Credit for Actions 

Performed in Compliance With 

Previous Service Information 

Two commenters, ExpressJet Airlines 

and Honeywell, request that credit be 

given for actions performed in 

compliance with previous service 

information. 

ExpressJet Airlines states that 

paragraph (l) of the NPRM calls for an 

inspection on any INU that is not 

identified in Table 2 of the NPRM. 

However, the NPRM does not take into 

account the units which have already 

been driven to Mod T status by 

Honeywell Service Bulletin 7510100– 

34–0037, dated July 8, 2004. ExpressJet 

requests that compliance with 

Honeywell Service Bulletin 7510100– 

34–0037 be considered as an alternative 

to the inspections required in paragraph 

(l) of the NPRM. 

Honeywell also commented on the 

same issue. Honeywell states that it is 

concerned that many airplanes have 

been inspected and verified to be 

compliant with AD 2006–22–05. 

Honeywell asks the FAA to clarify 

whether the intent of the NPRM was to 

require that all affected operators reinspect their airplanes. Honeywell also 

asks if the FAA can make a note under 

the compliance section to advise 

operators who actually complied with 

AD 2006–22–05 and verified their 

radios have modification AS and the 

new part number installed that they 

were already compliant with the new 

AD. 

We agree to provide clarification for 

both ExpressJet Airlines’ and 

Honeywell’s comments. Paragraph (l) of 

this AD applies only to any INUs that 

are not listed in Table 2 of this AD 

(which is the same list as Table 1 of AD 

2006–22–05). In addition, if operators 

have previously inspected INUs that are 

not listed in Table 2 and have 

accomplished the applicable actions 

specified in paragraph (l) of this AD, 

then those operators are already in 

compliance with paragraph (l) of this 

AD. According to paragraph (e) of this 

AD, the actions are required within the 

specified compliance time, unless 

already accomplished. Honeywell 

Service Bulletin 7510100–34–0037 only 

addresses the localizer fix. However, 

this AD requires that the glide slope be 

fixed in addition to the localizer. We 

will not consider compliance with 

Honeywell Service Bulletin 7510100– 

34–0037 as an alternative to the 

inspections required in paragraph (l) of 

the NPRM. No changes have been made 

to the final rule. 


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Federal Register / Vol. 75, No. 59 / Monday, March 29, 2010 / Rules and Regulations 15333 

Request To Remove Reference to 

Specific Revision of Service 

Information 

Honeywell requests that the FAA 

remove the reference to Revision 1, 

dated January 21, 2003, of the 

Honeywell Technical Newsletter (TNL) 

A23–3850–001 and simply reference the 

‘‘current revision.’’ The TNL is currently 

at Revision 6. Based on the release of 

this new AD, Honeywell states that it 

plans to update the TNL with current 

information and clarify how to interpret 

the AD. Honeywell states that it cannot 

release the update until the new AD is 

released. 

We disagree with Honeywell’s request 

to refer to the ‘‘current revision’’ of the 

TNL. The NPRM did not require the 

Honeywell TNL, but did require 

Honeywell Alert Service Bulletin 

7510100–34–A0035, dated July 11, 

2003; and Honeywell Service Bulletin 

7510100–34–0037, dated July 8, 2004; as 

the appropriate sources of service 

information to accomplish the required 

actions in this AD. Honeywell provided 

the TNL as a tool to communicate with 

its customers regarding this technical 

issue. We included the TNL in Note 3 

of the NPRM for reference only. To 

avoid confusion, we have removed Note 

3 of the NPRM, which referred to this 

TNL. 

Request To Revise Paragraph (j) of the 

NPRM 

Honeywell recommends wording 

changes to paragraph (j) of the NPRM to 

remove the sentence ‘‘If Mod T is 

installed, no further action is required 

by this paragraph.’’ 

We agree to remove the sentence ‘‘If 

Mod T is installed, no further action is 

required by this paragraph’’ from 

paragraph (j) of the NPRM. Although 

Honeywell provides no justification for 

this wording change, we agree that 

making this change provides further 

clarification. Doing Mod T repairs only 

the localizer in accordance with 

Honeywell Service Bulletin 7510100– 

34–0037, dated July 8, 2004. However, 

the intent of this AD is to require that 

the glide slope and the localizer be 

serviced. Doing Mod T repairs the 

localizer in accordance with Honeywell 

Service Bulletin 7510100–34–0037, 

dated July 8, 2004. The glide slope is 

addressed by accomplishing the actions 

in Honeywell Alert Service Bulletin 

7510100–34–A0034, dated February 28, 

2003. Honeywell Alert Service Bulletin 

7510100–34–A0035, dated July 11, 

2003, does not address the localizer; it 

provides instructions for changing the 

part number after the glide slope is 

repaired. The glide slope and the 

localizer repairs are accomplished 

independent from each other in 

different Honeywell service bulletins. 

Therefore, we have revised paragraph 

(j) of this AD by adding the text ‘‘* * * 

(which relates to the glide slope fix) 

***’’ to the sentence that begins ‘‘If 

Mod L, N, P, or R is installed * * *’’ 

and adding ‘‘if Mod T is not installed 

(which relates to the localizer fix), 

within 30 months after December 1, 

2006, do all applicable related 

investigative, corrective, and other 

specified actions in accordance with the 

Accomplishment Instructions * * *’’ in 

that same sentence (before ‘‘Honeywell 

Service Bulletin 7510100–34–0037, 

dated July 8, 2004’’). We made this 

change to clarify that Honeywell Service 

Bulletin 7510100–34–0037, dated July 8, 

2004, addresses the localizer fix. This 

change does not increase the scope of 

this AD. 

Request To Include Additional Service 

Information 

Honeywell requests that we add 

Honeywell Alert Service Bulletin 

7510134–34–A0017, dated July 11, 

2003, to Table 1 in the NPRM. 

We agree to include Honeywell Alert 

Service Bulletin 7510134–34–A0017, 

dated July 11, 2003, in Table 1 of this 

final rule to maintain consistency 

because the other service bulletins 

included in Table 1 of this AD were 

issued in pairs. Honeywell Alert Service 

Bulletin 7510100–34–A0034, dated 

February 28, 2003, was paired with 

Honeywell Alert Service Bulletin 

7510134–34–A0016, Revision 001, 

dated March 4, 2003. Honeywell Service 

Bulletin 7510100–34–0037, dated July 8, 

2004, was paired with Honeywell 

Service Bulletin 7510134–34–0018, 

dated July 8, 2004. Adding Honeywell 

Alert Service Bulletin 7510134–A0017, 

does not change any requirements of 

this AD, because Honeywell Alert 

Service Bulletin 7510134–34–A0017 is a 

prerequisite to Honeywell Alert Service 

Bulletin 7510100–34–A0035, dated July 

11, 2003, and Honeywell Alert Service 

Bulletin 7510100–34–A0035 refers to 

Honeywell Alert Service Bulletin 

7510134–34–A0017. 

We contacted Honeywell for more 

information about the technical content 

of Honeywell Alert Service Bulletin 

7510134–34–A0017, dated July 11, 

2003. Honeywell Alert Service Bulletin 

7510100–34–A0035, dated July 11, 

2003, references Honeywell Alert 

Service Bulletin 7510134–34–A0017, 

dated July 11, 2003, as a source of 

service information on the new part 

numbers assigned after performing 

Honeywell Alert Service Bulletin 

7510100–34–A0034, dated February 28, 

2003. We have added Honeywell Alert 

Service Bulletin 7510134–34–A0017, 

dated July 11, 2003, to Table 1 of this 

AD. This does not increase the financial 

burden on operators, nor does it 

increase the scope of the AD. 

Request To Add Part Numbers 

Honeywell requests that we revise 

paragraph (l) of the NPRM to list part 

numbers 7510134–611, –631, –701, and 

–731; which are parts of the Honeywell 

Primus II RNZ–850( )/–851( ) INU after 

modification; to the inspection to 

determine whether Mod L, N, P, R, or 

T is installed. 

We agree to provide clarification. We 

have revised paragraphs (l), (l)(1), (l)(2), 

and (l)(3) of this AD to specify the NRM 

part numbers 7510134–611, –631, –701, 

and –731 instead of the modification 

level. Paragraphs (l)(1) and (l)(2) of this 

AD correctly specify which combination 

of part number and modification level 

meets the technical requirements of the 

modification. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Explanation of Changes to This AD 

We have changed the product 

identification line in the body of this 

AD to specify the design approval 

holder of the affected appliance rather 

than ‘‘various aircraft.’’ 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Explanation of Change to Costs of 

Compliance 

After the NPRM was issued, we 

reviewed the figures we have used over 

the past several years to calculate AD 

costs to operators. To account for 

various inflationary costs in the airline 

industry, we find it necessary to 

increase the labor rate used in these 

calculations from $80 per work hour to 

$85 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly labor 

rate. 

Costs of Compliance 

There are about 3,063 aircraft of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 


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15334 Federal Register / Vol. 75, No. 59 / Monday, March 29, 2010 / Rules and Regulations 

comply with this AD. The manufacturer states that it will supply required parts 

to existing customers at no cost. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

aircraft 

Number of 

U.S.-registered 

aircraft 

Fleet cost 

Inspection for NRM modification level ...... 1 $85 $0 $85 Up to 1,500 ............. Up to $127,500. 

AFM revision ............................................. 1 85 0 85 Up to 1,500 ............. Up to 127,500. 

Modification (to Mod T configuration) ....... 1 85 0 85 Up to 1,500 ............. Up to 127,500. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the proposed actions specified in this 

final rule, and that no operator would 

accomplish those actions in the future if 

this AD were not adopted. We have 

been advised, however, that the actions 

have already been done on some 

affected airplanes. Therefore, the future 

economic cost impact of this rule on 

U.S. operators is expected to be less 

than the cost impact figures indicated 

above. 

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 amendment 39–14802 (71 

FR 62907, October 27, 2006) and by 

adding the following new airworthiness 

directive (AD): 

2010–07–02 Honeywell, Inc.: Amendment 

39–16246. Docket No. FAA–2008–0556; 

Directorate Identifier 2007–NM–028–AD. 

Effective Date 

(a) This AD becomes effective May 3, 2010. 

Affected ADs 

(b) This AD supersedes AD 2006–22–05, 

Amendment 39–14802. 

Applicability 

(c) This AD applies to various aircraft, 

certificated in any category, equipped with 

any Honeywell Primus II RNZ–850( )/– 

851( ) integrated navigation units (INUs) 

identified in a service bulletin identified in 

Table 1 of this AD. The aircraft include, but 

are not limited to, BAE Systems (Operations) 

Limited (Jetstream) Model 4101 airplanes; 

Bombardier Model BD–700–1A10 airplanes; 

Bombardier Model CL–215–6B11 (CL–415 

variant) airplanes; Cessna Model 560, 560XL, 

and 650 airplanes; Dassault-Aviation Model 

Mystere-Falcon 50 airplanes; 328 Support 

Services GmbH (Dornier) Model 328–100 and 

–300 airplanes; Empresa Brasileira de 

Aeronautica S.A. (EMBRAER) Model EMB– 

135 airplanes and Model EMB–145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP airplanes; Learjet Model 45 airplanes; 

Hawker Beechcraft Corporation Model 

Hawker 800XP and Hawker 1000 airplanes; 

and Sikorsky Model S–76A, S–76B, and 

S–76C aircraft. 

TABLE 1—SERVICE BULLETINS AFFECTED BY THIS AD 

INUs listed in Honeywell— Revision— Dated— 

(1) Alert Service Bulletin 7510134–34–A0016 ....................................................... 001 ........................................................ March 4, 2003. 

(2) Alert Service Bulletin 7510134–34–A0017 ....................................................... Original .................................................. July 11, 2003. 

(3) Service Bulletin 7510134–34–0018 .................................................................. Original .................................................. July 8, 2004. 

(4) Alert Service Bulletin 7510100–34–A0034 ....................................................... Original .................................................. February 28, 2003. 

(5) Alert Service Bulletin 7510100–34–A0035 ....................................................... Original .................................................. July 11, 2003. 

(6) Service Bulletin 7510100–34–0037 .................................................................. Original .................................................. July 8, 2004. 


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Note 1: This AD applies to Honeywell 

Primus II RNZ–850( )/–851( ) INUs installed 

on any aircraft, regardless of whether the 

aircraft has been otherwise modified, altered, 

or repaired in the area subject to the 

requirements of this AD. For aircraft that 

have been modified, altered, or repaired so 

that the performance of the requirements of 

this AD is affected, the owner/operator must 

request approval for an alternative method of 

compliance in accordance with paragraph (o) 

of this AD. The request should include an 

assessment of the effect of the modification, 

alteration, or repair on the unsafe condition 

addressed by this AD; and, if the unsafe 

condition has not been eliminated, the 

request should include specific proposed 

actions to address it. 

Unsafe Condition 

(d) This AD results from reports indicating 

that erroneous localizer and glideslope 

indications have occurred on certain aircraft 

equipped with the subject INUs. We are 

issuing this AD to ensure that the flightcrew 

has accurate localizer and glideslope 

deviation indications. An erroneous localizer 

or glideslope deviation indication could lead 

to the aircraft making an approach off the 

localizer, which could result in impact with 

an obstacle or terrain. 

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. 

Restatement of Certain Requirements of AD 

2006–22–05 

Compliance Time for Action 

(f) For any INU identified in Table 2 of this 

AD: Within 5 days after March 11, 2003 (the 

effective date of AD 2003–04–06, 

Amendment 39–13054, which was 

superseded by AD 2006–22–05), accomplish 

the requirements of either paragraph (g) or (h) 

of this AD. After December 1, 2006 (the 

effective date of AD 2006–22–05), only 

accomplishing the requirements of paragraph 

(g) of this AD is acceptable for compliance 

with this paragraph. 

TABLE 2—INUS IDENTIFIED IN AD 

2006–22–05 

P/N 7510100–811 through 7510100–814 

inclusive. 

P/N 7510100–831 through 7510100–834 

inclusive. 

P/N 7510100–901 through 7510100–904 

inclusive. 

P/N 7510100–911 through 7510100–914 

inclusive. 

P/N 7510100–921 through 7510100–924 

inclusive. 

P/N 7510100–931 through 7510100–934 

inclusive. 

Inspection To Determine Part Number 

(g) For any INU identified in Table 2 of this 

AD: Perform a one-time general visual 

inspection of the modification plate for the 

Honeywell Primus II NV–850 Navigation 

Receiver Module (NRM); part number 

7510134–811, –831, –901, or –931; which is 

part of the Honeywell Primus II RNZ–850( )/ 

–851( ) INU; to determine if Mod L has been 

installed. The modification plate is located 

on the bottom of the Honeywell Primus II 

RNZ–850( )/–851( ) INU, is labeled NV–850, 

and contains the part number and serial 

number for the Honeywell Primus II NV–850 

NRM. If Mod T is installed, the letter will be 

blacked out. The Honeywell service bulletins 

listed in Table 1 of this AD are acceptable 

sources of service information for the 

inspection required by this paragraph. 

(1) If Mod L is installed, before further 

flight, do paragraph (h) or (j) of this AD. After 

December 1, 2006, only accomplishment of 

paragraph (j) is acceptable for compliance 

with this paragraph. 

Note 2: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance unless otherwise specified. 

A mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight, or droplight and may require 

removal or opening of access panels or doors. 

Stands, ladders, or platforms may be required 

to gain proximity to the area being checked.’’ 

Aircraft Flight Manual (AFM) Revision 

(h) For aircraft having an INU identified in 

Table 2 of this AD: Revise the Limitations 

section of the AFM to include the following 

statements (which may be accomplished by 

inserting a copy of the AD into the AFM): 

‘‘FLIGHT LIMITATIONS 

When crossing the Outer Marker on 

glideslope, the altitude must be verified with 

the value on the published procedure. 

For aircraft with a single operating 

glideslope receiver, the approach may be 

flown using normal procedures no lower 

than Localizer Only Minimum Descent 

Altitude (MDA). 

For aircraft with two operating glideslope 

receivers, the aircraft may be flown to the 

published minimums for the approach using 

normal procedures if both glideslope 

receivers are tuned to the approach and both 

crew members are monitoring the approach 

using independent data and displays.’’ 

Parts Installation 

(i) For aircraft having an INU identified in 

Table 2 of this AD: As of March 11, 2003, no 

person may install a Honeywell Primus II 

NV–850 NRM on which Mod L has been 

installed, on the Honeywell Primus II RNZ– 

850( )/–851( ) INU of any aircraft, unless 

paragraph (h) or (j) of this AD is 

accomplished. As of December 1, 2006, only 

accomplishment of paragraph (j) is 

acceptable for compliance with this 

paragraph. 

Inspection To Determine Modification Level 

of NRM 

(j) For any INU identified in Table 2 of this 

AD on which Mod L was found to be 

installed during the inspection required by 

paragraph (g) of this AD, or for aircraft on 

which paragraph (h) of this AD was 

accomplished: Within 30 months after 

December 1, 2006, do an inspection of the 

modification plate on the Honeywell Primus 

II NV–850 NRM; part number 7510134–811, 

–831, –901, or –931; which is part of the 

Honeywell Primus II RNZ–850( )/–851( ) 

INU; to determine if Mod L, N, P, R, or T is 

installed. The modification plate located on 

the bottom of the Honeywell Primus II RNZ– 

850( )/–851( ) INU is labeled NV–850, and 

contains the part number and serial number 

for the Honeywell Primus II NV–850 NRM. 

If Mod L, N, P, R, or T is installed, the 

corresponding letter on the modification 

plate will be blacked out. Honeywell Alert 

Service Bulletin 7510100–34–A0035, dated 

July 11, 2003; and Honeywell Service 

Bulletin 7510100–34–0037, dated July 8, 

2004; are acceptable sources of service 

information for this inspection. If Mod L, N, 

P, or R is installed (which relates to the glide 

slope fix), within 30 months after December 

1, 2006, do all applicable related 

investigative, corrective, and other specified 

actions, in accordance with the 

Accomplishment Instructions of Honeywell 

Alert Service Bulletin 7510100–34–A0035, 

dated July 11, 2003; and if Mod T is not 

installed (which relates to the localizer fix), 

within 30 months after December 1, 2006, do 

all applicable related investigative, 

corrective, and other specified actions, in 

accordance with the Accomplishment 

Instructions of Honeywell Service Bulletin 

7510100–34–0037, dated July 8, 2004; to 

ensure that the NRM is at the Mod T 

configuration. Once the actions in this 

paragraph are completed, the AFM revision 

required by paragraph (h) of this AD may be 

removed from the AFM. 

(k) If the inspection specified in paragraph 

(j) of this AD is done within the compliance 

time specified in paragraph (f) of this AD, 

paragraph (g) of this AD does not need to be 

done. 

New Requirements of This AD 

Inspection To Determine Mod Level 

(l) For any INU that is not identified in 

Table 2 of this AD: Within 30 months after 

the effective date of this AD, perform a onetime general visual inspection of the 

modification plate for the Honeywell Primus 

II NV–850 Navigation Receiver Module 

(NRM); part number 7510134–611, –631, 

–701, –731, 811, –831, –901, or –931; which 

is part of the Honeywell Primus II RNZ– 

850()/–851() INU; to determine whether Mod 

L, N, P, R, or T is installed. The modification 

plate located on the bottom of the Honeywell 

Primus II RNZ–850()/–851() INU is labeled 

NV–850, and contains the part number and 

serial number for the Honeywell Primus II 

NV–850 NRM. If Mod L, N, P, R, or T is 

installed, the corresponding letter on the 

modification plate will be blacked out. 

Honeywell Alert Service Bulletin 7510100– 

34–A0035, dated July 11, 2003; and 

Honeywell Service Bulletin 7510100–34– 

0037, dated July 8, 2004; are acceptable 

sources of service information for this 

inspection. 

(1) If the NRM is part number 7510134– 

611, –631, –701, or –731, and has Mod T 


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15336 Federal Register / Vol. 75, No. 59 / Monday, March 29, 2010 / Rules and Regulations 

installed: No further action is required by 

this paragraph. 

(2) If the NRM is part number 7510134– 

611, –631, –701, or –731, and Mod T is not 

installed, within 30 months after the effective 

date of this AD: Do all applicable related 

investigative, corrective, and other specified 

actions, in accordance with the 

accomplishment Instructions of Honeywell 

Service Bulletin 7510100–34–0037, dated 

July 8, 2004; to ensure that the NRM is at the 

Mod T configuration. 

(3) If the NRM is part number 7510134– 

811, –831, –901, or –931: Within 30 months 

after the effective date of this AD, do all 

applicable related investigative, corrective, 

and other specified actions, in accordance 

with the Accomplishment Instructions of 

Honeywell Alert Service Bulletin 7510100– 

34–A0035, dated July 11, 2003; and 

Honeywell Service Bulletin 7510100–34– 

0037, dated July 8, 2004; to ensure that the 

NRM part number has been updated to 

7510134–611, –631, –701, –731 configuration 

and Mod T has been installed. 

Parts Installation 

(m) As of the effective date of this AD, no 

person may install a Honeywell Primus II 

RNZ–850()/–851() INU that contains a NV– 

850 NRM part number 7510134–811, –831, 

–901, or –931; or part number 7510134–611, 

–631, –701, or –731, that does not have Mod 

T installed, unless paragraph (l) is 

accomplished. 

No Report 

(n) Where Honeywell Alert Service 

Bulletin 7510100–34–A0035, dated July 11, 

2003 (or any of the related service 

information referenced therein), specifies to 

submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) The Manager, Los Angeles Aircraft 

Certification Office, 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: Daniel Bui, 

Aerospace Engineer, Systems and Equipment 

Branch, ANM–130L, FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; telephone (562) 627–5339; fax (562) 

627–5210. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(p) You must use the service information 

contained in Table 3 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. (Only 

the first page of these documents specifies 

the revision level of the document; no other 

page contains this information.) 

TABLE 3—ALL MATERIAL INCORPORATED BY REFERENCE

Honeywell— Revision— Dated— 

Alert Service Bulletin 7510134–34–A0016 001 ........................................................................... March 4, 2003. 

Alert Service Bulletin 7510134–34–A0017 Original .................................................................... July 11, 2003. 

Alert Service Bulletin 7510100–34–A0034 Original .................................................................... February 28, 2003. 

Alert Service Bulletin 7510100–34–A0035 Original .................................................................... July 11, 2003. 

Service Bulletin 7510100–34–0037 Original .................................................................... July 8, 2004. 

Service Bulletin 7510134–34–0018 Original .................................................................... July 8, 2004. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 4 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 4—NEW MATERIAL INCORPORATED BY REFERENCE

Honeywell— Revision— Dated— 

Alert Service Bulletin 7510134–34–A0016 001 ........................................................................... March 4, 2003. 

Alert Service Bulletin 7510134–34–A0017 Original .................................................................... July 11, 2003. 

Alert Service Bulletin 7510100–34–A0034 Original .................................................................... February 28, 2003. 

Service Bulletin 7510134–34–0018 Original .................................................................... July 8, 2004. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Honeywell Alert Service Bulletin 

7510100–34–A0035, dated July 11, 2003; and 

Honeywell Service Bulletin 7510100–34– 

0037, dated July 8, 2004; on December 1, 

2006 (71 FR 62907, October 27, 2006). 

(3) For service information identified in 

this AD, contact Honeywell Technical 

Operations Center, 1944 East Sky Harbor 

Circle, Phoenix, AZ 85034–3442; telephone 

(US & Canada) 800–601–3099, (International) 

602–365–3099; Internet http:// 

www.honeywell.com. 

(4) You may review copies of the service 

information at the Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 

17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6547 Filed 3–26–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 157 

[Docket No. RM05–1–002] 

Regulations Governing the Conduct of 

Open Seasons for Alaska Natural Gas 

Transportation Projects 

March 18, 2010. 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Final rule. 

SUMMARY: The Commission is amending 

its regulations, in order to clarify them 

in response to Order Nos. 717 and 717– 


PWALKER on DSK8KYBLC1PROD with RULES